AIR FORCE17.1 Small Business Innovation Research (SBIR)

Phase I Proposal Submission Instructions

INTRODUCTION

The Air Force (AF) proposal submission instructions are intended to clarify the Department of Defense (DoD) instructions as they apply to AF requirements. Firms must ensure their proposal meets all requirements of the announcement currently posted on the DoD website at the time the announcement closes.

The AF Program Manager is Mr. David Shahady. The AF SBIR/STTR Program Office can be contacted at 1-800-222-0336. For general inquiries or problems with the electronic submission, contact the DoD SBIR/STTR Help Desk at [1-800-348-0787] or Help Desk email at sbirhelp@bytecubed.com (9:00 a.m. to 6:00 p.m. ET Monday through Friday). For technical questions about the topics during the pre-announcement period (30 Nov 2016 through 09 Jan 2017), contact the Topic Authors listed for each topic on the Web site. For information on obtaining answers to your technical questions during the formal announcement period (10 Jan 2017 through 8 Feb 2017), go to https://sbir.defensebusiness.org.

General information related to the AF Small Business Program can be found at the AF Small Business website, http://www.airforcesmallbiz.org. The site contains information related to contracting opportunities within the AF, as well as business information, and upcoming outreach/conference events. Other informative sites include those for the Small Business Administration (SBA), www.sba.gov, and the Procurement Technical Assistance Centers, http://www.aptacus.us.org. These centers provide Government contracting assistance and guidance to small businesses, generally at no cost.

PHASE I PROPOSAL SUBMISSIONThe Air Force SBIR/STTR Program Office has instituted new requirements in an initiative to combat fraud in the SBIR/STTR program.  As a result, each Small Business is required to visit the AF SBIR Program website and read through the "Compliance with Small Business Innovation Research (SBIR) and Small Business Technology Transfer (STTR) Program Rules” training located at the bottom of this page: www.wpafb.af.mil/AFSBIRSTTR. The Certificate of Training Completion at the end of the training presentation and/or as pg. AF-9 of this document, MUST be signed by an official of your company, AND ATTACHED to your proposal.  Failure to do this will result in your proposal being removed from consideration. 

Read the DoD program announcement at https://sbir.defensebusiness.org/ for program requirements . When you prepare your proposal, keep in mind that Phase I should address the feasibility of a solution to the topic. For the AF, the contract period of performance for Phase I shall be nine (9) months, and the award shall not exceed $150,000. We will accept only one Cost Volume per Topic Proposal and it must address the entire nine-month contract period of performance.

The Phase I award winners must accomplish the majority of their primary research during the first six months of the contract with the additional three months of effort to be used for generating final reports. Each AF organization may request Phase II proposals prior to the completion of the first six months of the contract based upon an evaluation of the contractor’s technical progress and review by the AF technical point of contact utilizing the criteria in section 6.0 of the DoD announcement. The last three months of the nine-month Phase I contract will provide project continuity for all Phase II award winners so no modification to the Phase I contract should be necessary.

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Limitations on Length of Proposal

The Phase I Technical Volume has a 20-page-limit (excluding the Cover Sheet, Cost Volume, Cost Volume Itemized Listing (a-j), Company Commercialization Report, Non-Disclosure Agreement Form and Certificate of Training Completion Form) The Technical Volume must be in no type smaller than 10-point on standard 8-1/2" x 11" paper with one (1) inch margins.  Only the Technical Volume and any enclosures or attachments count toward the 20-page limit.  In the interest of equity, pages in excess of the 20-page limitation will not be considered for review or award.

Phase I Proposal Format

Proposal Cover Sheet: If your proposal is selected for award, the technical abstract and discussion of anticipated benefits will be publicly released on the Internet; therefore, do not include proprietary information in these sections.

Technical Volume: The Technical Volume should include all graphics and attachments but should not include the Cover Sheet or Company Commercialization Report as these items are completed separately. Most proposals will be printed out on black and white printers so make sure all graphics are distinguishable in black and white. To verify that your proposal has been received, click on the “Check Upload” icon to view your proposal. Typically, your uploaded file will be virus checked. If your proposal does not appear after an hour, please contact the DoD SBIR/STTR Help Desk at [1-800-348-0787] or Help Desk email at sbirhelp@bytecubed.com (9:00 am to 6:00 pm ET Monday through Friday).

Key Personnel: Identify in the Technical Volume all key personnel who will be involved in this project; include information on directly related education, experience, and citizenship. A technical resume of the principle investigator, including a list of publications, if any, must be part of that information. Concise technical resumes for subcontractors and consultants, if any, are also useful. You must identify all U.S. permanent residents to be involved in the project as direct employees, subcontractors, or consultants. You must also identify all non-U.S. citizens expected to be involved in the project as direct employees, subcontractors, or consultants. For all non-U.S. citizens, in addition to technical resumes, please provide countries of origin, the type of visa or work permit under which they are performing and an explanation of their anticipated level of involvement on this project, as appropriate. You may be asked to provide additional information during negotiations in order to verify the foreign citizen’s eligibility to participate on a contract issued as a result of this announcement.

Phase I Work Plan Outline

NOTE: THE AF USES THE WORK PLAN OUTLINE AS THE INITIAL DRAFT OF THE PHASE I STATEMENT OF WORK (SOW). THEREFORE, DO NOT INCLUDE PROPRIETARY INFORMATION IN THE WORK PLAN OUTLINE. TO DO SO WILL NECESSITATE A REQUEST FOR REVISION AND MAY DELAY CONTRACT AWARD.

At the beginning of your proposal work plan section, include an outline of the work plan in the following format:

Scope: List the major requirements and specifications of the effort.Task Outline: Provide a brief outline of the work to be accomplished over the span of the Phase I effort.Milestone Schedule

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DeliverablesKickoff meeting within 30 days of contract startProgress reportsTechnical review within 6 monthsFinal report with SF 298

Cost Volume

Cost Volume information should be provided by completing the on-line Cost Volume form and including the Cost Volume Itemized Listing specified below. The Cost Volume detail must be adequate to enable Air Force personnel to determine the purpose, necessity and reasonability of each cost element. Provide sufficient information (a-j below) on how funds will be used if the contract is awarded. The on-line Cost Volume and Itemized Cost Volume Information will not count against the 20-page limit. The itemized listing may be placed in the “Explanatory Material” section of the on-line Cost Volume form (if enough room), or as the last page(s) of the Technical Volume Upload. (Note: Only one file can be uploaded to the DoD Submission Site). Ensure that this file includes your complete Technical Volume and the information below.

a. Special Tooling and Test Equipment and Material: The inclusion of equipment and materials will be carefully reviewed relative to need and appropriateness of the work proposed. The purchase of special tooling and test equipment must, in the opinion of the Contracting Officer, be advantageous to the Government and relate directly to the specific effort. They may include such items as innovative instrumentation and/or automatic test equipment.

b. Direct Cost Materials: Justify costs for materials, parts, and supplies with an itemized list containing types, quantities, and price and where appropriate, purposes.

c. Other Direct Costs: This category of costs includes specialized services such as machining or milling, special testing or analysis, costs incurred in obtaining temporary use of specialized equipment. Proposals, which include leased hardware, must provide an adequate lease vs. purchase justification or rational.

d. Direct Labor: Identify key personnel by name if possible or by labor category if specific names are not available. The number of hours, labor overhead and/or fringe benefits and actual hourly rates for each individual are also necessary.

e. Travel: Travel costs must relate to the needs of the project. Break out travel cost by trip, with the number of travelers, airfare, per diem, lodging, etc. The number of trips required, as well as the destination and purpose of each trip should be reflected. Recommend budgeting at least one (1) trip to the Air Force location managing the contract.

f. Cost Sharing: If proposing cost share arrangements, please note each Phase I contract total value may not exceed $150K total, while Phase II contracts shall have an initial Not to Exceed value of $750K. Please note that cost share contracts do not allow fees. NOTE: Subcontract arrangements involving provision of Independent Research and Development (IR&D) support are prohibited in accordance with Under Secretary of Defense (USD) memorandum “Contractor Cost Share”, dated 16 May 2001, as implemented by SAF/AQ memorandum, same title, dated 11 July 2001.

g. Subcontracts: Involvement of university or other consultants in the planning and/or research stages of the project may be appropriate. If the offeror intends such involvement, describe in detail and include information in the Cost Volume. The proposed total of all consultant fees, facility leases or usage fees,

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and other subcontract or purchase agreements may not exceed one-third of the total contract price or cost, unless otherwise approved in writing by the Contracting Officer. Support subcontract costs with copies of the subcontract agreements. The supporting agreement documents must adequately describe the work to be performed. At a minimum, an offeror must include a Statement of Work (SOW) with a corresponding detailed Cost Volume for each planned subcontract.

h. Consultants: Provide a separate agreement letter for each consultant. The letter should briefly state what service or assistance will be provided, the number of hours required and hourly rate.

i. Any exceptions to the model Phase I purchase order (P.O.) found at www.wpafb.af.mil/AFSBIRSTTR should be included in your cost proposal. Full text for the clauses included in the P.O. may be found at http://farsite.hill.af.mil.

NOTE: If no exceptions are taken to an offeror’s proposal, the Government may award a contract without discussions (except clarifications as described in FAR 15.306(a)). Therefore, the offeror’s initial proposal should contain the offeror’s best terms from a cost or price and technical standpoint. If selected for award, the award contract or P.O. document received by your firm may vary in format/content from the model P.O. reviewed. If there are questions regarding the award document, contact the Phase I Contracting Officer listed on the selection notification. The Government reserves the right to conduct discussions if the Contracting Officer later determines them to be necessary.

j. DD Form 2345: For proposals submitted under export-controlled topics (either International Traffic in Arms (ITAR) or Export Administration Regulations (EAR)), a copy of the certified DD Form 2345, Militarily Critical Technical Data Agreement, or evidence of application submission must be included. The form, instructions, and FAQs may be found at the United States/Canada Joint Certification Program website, http://www.dlis.dla.mil/jcp/. Approval of the DD Form 2345 will be verified if proposal is chosen for award.

NOTE: Only Government employees and technical personnel from Federally Funded Research and Development Centers (FFRDCs) MITRE and Aerospace Corporations, working under contract to provide technical support to AF Life Cycle Management Center and Space and Missiles Centers may evaluate proposals. All FFRDC employees have executed non-disclosure agreement (NDAs) as a requirement of their contracts. Additionally, AF support contractors may be used to administratively or technically support the Government’s SBIR Program execution. DFARS 252.227-7025, Limitations on the Use or Disclosure of Government-Furnished Information Marked with Restrictive Legends (May 2013), allows Government support contractors to do so without company-to-company NDAs only AFTER the support contractor notifies the SBIR firm of its access to the SBIR data AND the SBIR firm agrees in writing no NDA is necessary. If the SBIR firm does not agree, the “Yes” box should be checked, and a company-to-company NDA should also be submitted. The attached “NDA Requirements Form” must be completed, signed, and included, with your proposal indicating your firm’s determination regarding company-to-company NDAs for access to SBIR data by AF support contractors. Proposal packages that do not contain an Non-Disclosure Agreement (NDA) Requirements Form (pg. AF-8) will be considered incomplete, and will NOT be considered for award. This form will not count against the 20-page limitation.

k. The Air Force does not participate in the Discretionary Technical Assistance Program. Contractors should not submit proposals that include Discretionary Technical Assistance.

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PHASE I PROPOSAL SUBMISSION CHECKLIST

Failure to meet any of the criteria or to submit all required documents will result in your proposal being REJECTED and the Air Force will not evaluate your proposal. NOTE: If you are not registered in the System for Award Management, https://www.sam.gov/, you will not be eligible for an award.

1) The Air Force Phase I proposal shall be a nine-month effort and the cost shall not exceed $150,000.

2) The Air Force will accept only those proposals submitted electronically via the DoD SBIR Web site (https://sbir.defensebusiness.org/).

3) You must submit your Company Commercialization Report electronically via the DoD SBIR Web site (https://sbir.defensebusiness.org/).

It is mandatory that the complete proposal submission -- DoD Proposal Cover Sheet, Technical Volume with any appendices, Cost Volume, Itemized Cost Volume Information, and the Company Commercialization Report, Non-disclosure Agreement (NDA) Requirements Form,  (pg. AF-8) and Certificate of Training Completion Form -- be submitted electronically through the DoD SBIR Web site at https://sbir.defensebusiness.org/. Each of these documents is to be submitted separately through the Web site. Your complete proposal must be submitted via the submissions site on or before the 6:00 am ET, 8 Feb 2017 deadline.  A hardcopy will not be accepted.

The AF recommends that you complete your submission early, as computer traffic gets heavy near the announcement closing and could slow down the system. Do not wait until the last minute. The AF will not be responsible for proposals being denied due to servers being “down” or inaccessible. Please assure that your e-mail address listed in your proposal is current and accurate. The AF is not responsible for ensuring notifications are received by firms changing mailing address/e-mail address/company points of contact after proposal submission without proper notification to the AF. Changes of this nature that occur after proposal submission or award (if selected) for Phase I and II shall be sent to the Air Force SBIR/STTR site address, afprogram@afsbirsttr.net .

AIR FORCE PROPOSAL EVALUATIONS

The AF will utilize the Phase I proposal evaluation criteria in section 6.0 of the DoD announcement in descending order of importance with technical merit being most important, followed by the qualifications of the principal investigator (and team), followed by the potential for Commercialization Plan. The AF will utilize Phase II evaluation criteria in section 8.0 of the DoD announcement. Please note that where technical evaluations are essentially equal in merit, cost to the Government will be considered in determining the successful offeror. The next tie-breaker on essentially equal proposals will be the inclusion of manufacturing technology considerations.

The proposer's record of commercializing its prior SBIR and STTR projects, as shown in its Company Commercialization Report, will be used as a portion of the Commercialization Plan evaluation. If the "Commercialization Achievement Index (CAI)”, shown on the first page of the report, is at the 20th percentile or below, the proposer will receive no more than half of the evaluation points available under evaluation criterion (c) in Section 6 of the DoD 17.1 SBIR instructions. This information supersedes Paragraph 4, Section 5.4e, of the DoD 17.1 SBIR instructions.

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A Company Commercialization Report showing the proposing firm has no prior Phase II awards will not affect the firm's ability to win an award. Such a firm's proposal will be evaluated for commercial potential based on its commercialization strategy.

Proposal Status and Debriefings

The Principal Investigator (PI) and Corporate Official (CO) indicated on the Proposal Cover Sheet will be notified by e-mail regarding proposal selection or non-selection. The e-mail will include a link to a secure Internet page containing specific selection/non-selection information. Small Businesses will receive a notification for each proposal submitted. Please read each notification carefully and note the Proposal Number and Topic Number referenced. If changes occur to the company mail or email address(es) or company points of contact after proposal submission, the information should be provided to the AF at afprogram@afsbirsttr.net.

As is consistent with the DoD SBIR/STTR announcement, any debriefing requests must be submitted in writing, received within 30 days after receipt of notification of non-selection. Written requests for debrief must be sent to the Contracting Officer named on your non-selection notification. Requests for debrief should include the company name and the telephone number/e-mail address for a specific point of contract, as well as an alternate. Also include the topic number under which the proposal(s) was submitted, and the proposal number(s). Debrief requests received more than 30 days after receipt of notification of non-selection will be fulfilled at the Contracting Officers' discretion. Unsuccessful offerors are entitled to no more than one debriefing for each proposal.IMPORTANT: Proposals submitted to the AF are received and evaluated by different offices within the Air Force and handled on a Topic-by-Topic basis. Each office operates within their own schedule for proposal evaluation and selection. Updates and notification timeframes will vary by office and Topic. If your company is contacted regarding a proposal submission, it is not necessary to contact the AF to inquire about additional submissions. Additional notifications regarding your other submissions will be forthcoming.

We anticipate having all the proposals evaluated and our Phase I contract decisions within approximately three months of proposal receipt. All questions concerning the status of a proposal, or debriefing, should be directed to the local awarding organization SBIR Program Manager.

PHASE II PROPOSAL SUBMISSIONS

Phase II is the demonstration of the technology that was found feasible in Phase I. Only Phase I awardees are eligible to submit a Phase II proposal. All Phase I awardees will be sent a notification with the Phase II proposal submittal date and a link to detailed Phase II proposal preparation instructions, located here: https://www.wpafb.af.mil/afsbirsttr. Phase II efforts are typically 27 months in duration (24 months technical performance, with 3 additional months for final reporting), and an initial value not to exceed $750,000.

NOTE: Phase II awardees should have a Defense Contract Audit Agency (DCAA) approved accounting system. It is strongly urged that an approved accounting system be in place prior to the AF Phase II award timeframe. If you have questions regarding this matter, please discuss with your Phase I Contracting Officer.

All proposals must be submitted electronically at https://sbir.defensebusiness.org/ by the date indicated in the notification. The Technical Volume is limited to 50 pages (unless a different number is specified in the notification). The Commercialization Report, any advocacy letters, SBIR Environment Safety and Occupational Health (ESOH) Questionnaire, and Cost Volume Itemized Listing (a-i) will not count

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against the 50 page limitation and should be placed as the last pages of the Technical Volume file that is uploaded. (Note: Only one file can be uploaded to the DoD Submission Site. Ensure that this single file includes your complete Technical Volume and the additional Cost Volume information.) The preferred format for submission of proposals is Portable Document Format (.pdf). Graphics must be distinguishable in black and white. Please virus-check your submissions.

AIR FORCE SBIR PROGRAM MANAGEMENT IMPROVEMENTS

The AF reserves the right to modify the Phase II submission requirements. Should the requirements change, all Phase I awardees will be notified. The AF also reserves the right to change any administrative procedures at any time that will improve management of the AF SBIR Program.

AIR FORCE SUBMISSION OF FINAL REPORTS

All Final Reports will be submitted to the awarding AF organization in accordance with the Contract. Companies will not submit Final Reports directly to the Defense Technical Information Center (DTIC).

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AIR FORCE17.1 Small Business Innovation Research (SBIR)Non-Disclosure Agreement (NDA) Requirements

DFARS 252.227-7018(b)(8), Rights in Noncommercial Technical Data and Computer Software – Small Business Innovation Research (SBIR) Program (May 2013), allows Government support contractors access to SBIR data without company-to-company NDAs only AFTER the support contractor notifies the SBIR firm of its access to the SBIR data AND the SBIR firm agrees in writing no NDA is necessary. If the SBIR firm does not agree, a company-to-company NDA is required.

“Covered Government support contractor” is defined in 252.227-7018(a)(6) as “a contractor under a contract, the primary purpose of which is to furnish independent and impartial advice or technical assistance directly to the Government in support of the Government’s management and oversight of a program or effort (rather than to directly furnish an end item or service to accomplish a program or effort), provided that the contractor—

(i) Is not affiliated with the prime contractor or a first-tier subcontractor on the program or effort, or with any direct competitor of such prime contractor or any such first-tier subcontractor in furnishing end items or services of the type developed or produced on the program or effort; and

(ii) Receives access to the technical data or computer software for performance of a Government contract that contains the clause at 252.227-7025, Limitations on the Use or Disclosure of Government-Furnished Information Marked with Restrictive Legends.”

USE OF SUPPORT CONTRACTORS:

Support contractors may be used to administratively process SBIR documentation or provide technical support related to SBIR contractual efforts to Government Program Offices.

Below, please provide your firm’s determination regarding the requirement for company-to-company NDAs to enable access to SBIR documentation by Air Force support contractors. This agreement must be signed and included in your Phase I/II proposal package.

YES NO Non-Disclosure Agreement Required(If Yes, include your firm’s NDA requirements in your proposal)

Company: Proposal Number:

Address: City/State/Zip:

Proposal Title:

Name Date: _____________________

Title/Position

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AIR FORCE SMALL BUSINESS INNOVATION RESEARCH (SBIR)/SMALL BUSINESS TECHNOLOGY TRANSFER (STTR) PROGRAMS

“COMPLIANCE WITH SBIR/STTR PROGRAM RULES”

The undersigned has fully and completely reviewed this training on behalf of the proposer/awardee, understands the information presented, and has the authority to make this certification on behalf of the proposer/awardee. The undersigned understands providing false or misleading information during any part of the proposal, award, or performance phase of a SBIR or STTR contract or grant may result in criminal, civil or administrative sanctions, including but not limited to: fines, restitution, and/or imprisonment under 18 USC 1001; treble damages and civil penalties under the False Claims Act, 31 USC 3729 et seq.; double damages and civil penalties under the Program Fraud Civil Remedies Act, 31 USC 3801 et seq.; civil recovery of award funds; suspension and/or debarment from all federal procurement and non-procurement transactions, FAR Part 9.4 or 2 CFR Part 180; and other administrative remedies including termination of active SBIR/STTR awards.

________________________ _______________Signature Date

________________________Name

_________________________ ___________________Firm Name and Position Title Proposal Number

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AIR FORCE SBIR 17.1 Topic Index

AF171-001 Variable Pressure/Flow Control Firefighting NozzleAF171-002 Wide-angle RetroreflectometerAF171-003 Alternative Method of Surface Activation of High Strength Steels for ElectroplatingAF171-004 Electroplating 3D Printed MaterialsAF171-005 (This topic has been deleted from this Announcement)AF171-006 Development of Additive Manufacturing for Landing Gear ComponentsAF171-007 Real-time, 3-D Model Deformation Measurement Capability for Perforated Wall Wind

TunnelsAF171-008 Reduction/Elimination of Unsteady Aerodynamic Loads on Model and Balance Support

Systems in Large Scale Wind TunnelsAF171-009 Miniature Video Camera Technology for Embedded ProbesAF171-010 Non-Intrusive, Time-Resolved Turbulence Measurements in Large-Scale Hypersonic Wind

TunnelsAF171-011 Advanced, Low-Erosion Electrode Technologies for Arcjet TestingAF171-012 Air to Ground Target System for Engineering Based Airborne Electro-Optics Imaging

System PerformanceAF171-013 Next Gen Infrared Emitter Array PackagingAF171-014 Dynamic Aircraft Tire Footprint Sensor (DATFS)AF171-015 Infrared Light Emitting Diode Extraction EfficiencyAF171-016 Efficient On-Board Fire SuppressionAF171-017 Low Cost High Sensitivity Superconducting Magnetometers and GradiometersAF171-018 Gallium Oxide Homo/Hetero-Epitaxial Structures for RF and Power Switching DevicesAF171-019 High-Speed Wind Tunnel Transient Dynamics During Start-upAF171-020 Instrumentation for carbon-carbon structures in extreme environmentsAF171-021 Ultradense Plasmonic Integrated Devices and CircuitsAF171-022 Advanced back-illuminated CMOS image sensors for adaptive optics applicationsAF171-023 Adaptive Optics Prototype for a Meter-class Telescope used for Space SurveillanceAF171-024 Daylight Glare Reduction Using a Light-field CameraAF171-025 Realtime Multiframe Blind Deconvolution (MFBD) for Imaging through TurbulenceAF171-026 24/7 Monitoring of Active Satellites using Passive Radio-Frequency (RF) SensorsAF171-027 Cyber warfare laboratory designAF171-028 Cyber Attack model using game theoryAF171-029 Training for Cyber OperationsAF171-030 Battlefield Airmen Augmented Reality System (BAARS)AF171-031 Wearable, Broadband, EM Field Exposure Detection System with Data Sharing CapabilityAF171-032 Wearable Device to Characterize Chemical Hazards for Total Exposure HealthAF171-033 Mobile activity tracking system for field training and exercise assessmentAF171-034 Simulator Common Architecture Requirements and Standards (SCARS)AF171-035 Data Growth Within the Air Force Weather EnterpriseAF171-036 Energy Efficient Technologies for Tactical Communications and Networking (E2-COMS)AF171-037 Mission Assured Authentication (MAA)AF171-038 High-Throughput High-Frequency (HTHF) Battle Management Command-Control (BMC2)AF171-039 Data Protection and Sharing Technologies In Critical Key Networks and for Cyber Defense

of Weapons (DPSTICK)AF171-040 Aerial Cloud Analytics for Strategic and Tactical Warfighting (ACAST)AF171-041 Aerial Cloud Computing Technologies (ACCT)AF171-042 Big Data Cyber AnalyticsAF171-043 Mobile User Objective System (MUOS) for Moderate Data Rate Communications (MMDR)AF171-044 Mobile Authentication and Access CapabilityAF171-045 Automatic Dependent Surveillance - Broadcast (ADS-B) and UAS operationsAF171-046 3rd Party Intellectual Property (I V&V Effort)AF171-047 Resilient Communications for Contested Autonomous Manned/Unmanned Teaming

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AF171-048 Big Data Analytics for Activity Based IntelligenceAF171-049 Collective Human Intelligence as Exploitation Layer in Automated Information SystemsAF171-050 Human-Machine Collaboration for Automated Patterns of Life AnalysisAF171-051 Elevated Situational Awareness through Discovery and Characterization of Composable Free

Market AnalyticsAF171-052 Non Intrusive Passive Optics/Imaging for Damage Prediction and Structural Health

Monitoring in Gas TurbinesAF171-053 Extrapolating Useful Life from Composite Structures Using In-Service DataAF171-054 Non-GPS Relative Navigation for Remotely Piloted Aircraft (RPA) RefuelingAF171-055 Fast High Resolution, High Contrast Microfocus X-Ray Computed Tomography

Reconstruction Algorithms for ICBM ComponentsAF171-056 Fiber Optic Sensing Systems (FOSS) for Expendable Launch VehiclesAF171-057 Dynamic and Efficient Vapor Compressor for Aircraft Thermal Management Systems

(TMSs)AF171-058 Non-Persistent Tracers for Particle Image Velocimetry in High-Mach Number Wind TunnelsAF171-059 Sustainable High-temperature Hybrid Turbine RotorsAF171-060 Novel, Tactical-Sized Reconfigurable Aerial Refueling BoomAF171-061 Micro Reactor Synthesis of Energetic Ionic LiquidsAF171-062 Sensor Open System Architecture (SOSA) Architectural ResearchAF171-063 Electronically Controlled Adaptive Polarization for Compact Broadband Transmitters and

ReceiversAF171-064 Energy Storage SystemAF171-065 Effects of GPS Degraded or Denied Environments on Delivery VehiclesAF171-066 Real-Time Threat DatabaseAF171-067 Miniaturization of Comprehensive Energetic Charged Particle Detectors for Anomaly

AttributionAF171-068 Non Destructive Trusted FPGA VerificationAF171-069 Improved Data Fusion Techniques for Space-Based Remote SensingAF171-070 Advanced Solar Cell MetallizationAF171-071 Integration of Tactical and Individual Satellite Operations with Global Operation and ControlAF171-072 Integrated Photon Management for Multijunction Solar CellsAF171-073 Weather SatelliteAF171-074 Agile Inspector SatelliteAF171-075 Assured Autonomous Spacecraft GN&C via Hybrid ControlAF171-076 Wideband GPS Digital Payload ArchitectureAF171-077 Cyber Vulnerabilities & Mitigations in the Radio Frequency DomainAF171-078 SWIR-LWIR detectors employing Unipolar Barrier ArchitecturesAF171-079 Automatic Exploitation of Energetic Charged Particle Sensor DataAF171-080 Dual Band Focal Plane ArrayAF171-081 Low-Light SWIR Vision SystemsAF171-082 Modeling and Simulation of Complex Multiphase Interaction of Energetic MaterialsAF171-083 High-g MEMS Accelerometer Sensor for Hard Target ApplicationsAF171-084 Advanced Bio-inspired Imaging System with Multiple Optical Sensing ModesAF171-085 Small Munitions Advanced Seeker Handoff (SMASH)AF171-086 Full-size Warhead Computed TomographyAF171-087 FRM Automated Development (FAD)AF171-088 Reactive Composite Materials for Asymmetric Shock Propagation in Multi-Functional

WeaponsAF171-089 High Voltage (HV) Fireset Systems and Subsystem Component Level DesignsAF171-090 Deep Learning Tools and Architectures for Munitions (DeLTA-M)AF171-091 Corrosion Indicating Coatings for Aircraft Bilges and Wheel WellsAF171-092 Coating Additives for Enhanced Laser De-paintAF171-093 Low Hyrdrogen Embrittlement (LHE) Brush Plating Chemistries for Cadmium (Cd)

ReplacementAF171-094 Improved Non-Damaging Method of Removing Powder Coating SystemAF171-095 Computational corrosion modeling for Condition Based Maintenance Plus (CBM+)/aircraft

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environment trackingAF171-096 Improved Casting Quality through Novel Engineered Ceramic Molten Metal Filters

Improved Casting Quality through Additively Manufactured Ceramic Molten Metal FiltersAF171-097 High temperature moisture sealants for hot exhuast structures on advanced systemAF171-098 Quantification of microtexture regions in titanium alloys using optical sensing methodsAF171-099 Diffusely Scattering Paints for Remotely Piloted AircraftAF171-100 Manufacturing and Metrology of High Magnetic Permeability Materials for High Efficiency,

Wideband, and Conformal RF AntennasAF171-101 Additive Manufacturing of Freeform Optical Elements for Imaging System Weight and

Volume ReductionAF171-102 Portable, Precision Automated Welding for Aerospace AlloysAF171-103 Tailpipe Coating Thickness Measurement CapabilityAF171-104 Portable, Localized Low Observable (LO) Coating Removal ToolAF171-105 High Altitude Electromagnetic Pulse (HEMP) Protection for Nuclear Command and Control

Communications (NC3) SystemsAF171-106 Improved manufacturing and design of liquid electrolyte delivery systemsAF171-107 Continuously Self-Leveling Weapons-Storage Support StructureAF171-108 All-Fiber Optical Isolators for High Energy LasersAF171-109 Structural Directed Energy and Nuclear Effect Mitigation of Composite Aeroshells for

MunitionsAF171-110 Additive Manufacturing Process for High Resolution Conductive TracesAF171-111 Nondestructive Quantification of the Degraded Elastic Modulus and Poisson's Ratio of

Impact Damaged Polymer Matrix CompositesAF171-112 Thermal Modeling Base High-Temperature Polymer Matrix Composite (PMC) Structural

RepairAF171-113 Solid-State Amplifier/Transmitter replacements for Travelling Wave Tube (TWT)

TechnologyAF171-114 Enhancing Systems Engineering for Complex Systems with Digital ThreadAF171-115 3-D Antenna Technology using Additive ManufacturingAF171-116 Scalable Coherent Photonic Array on a Silicon PlatformAF171-117 Multi-Sensor/Multi-Platform Integration and Sensor Resource ManagementAF171-118 Develop a Small Pitch LADAR Receiver for Low SWAP SensingAF171-119 NIIRS 9 Small Unmanned Aircraft System (SUAS) 5-Inch GimbalAF171-120 Direct Measurement of Targeting Coordinates from Small Unmanned Aerial Systems

(SUAS) EO/IR Gimbal SystemsAF171-121 Integrated Circuit (IC) Die Extraction and Reassembly (DER) for More Complicated ICsAF171-122 V/W-band Accelerated Life Test SystemAF171-123 Dual Ka/Q-Band Low Noise AmplifiersAF171-124 Ultra-Endurance UAVAF171-125 Aerial Refueling of UAVsAF171-126 Integrable high-performance analog optical modulatorsAF171-127 Programmable Feed to Enable Low Frequency Measurements in Small Compact Far-Field

Antenna RangesAF171-128 Advanced Analog-to-Digital Converter for GPS ReceiversAF171-129 Focal Plane Arrays (FPAs) for Coherent LadarAF171-130 Small Unmanned Aircraft System (SUAS) 5-Inch Gimbal with Full Motion Video and

Hyperspectral

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AIR FORCE SBIR 17.1 Topic Descriptions

AF171-001 TITLE: Variable Pressure/Flow Control Firefighting Nozzle

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop a hose-end nozzle system capable of allowing the operator to hand select discharges of Ultrahigh-Pressure (UHP; 1100 to 1500 PSI @ 15 to 20 GPM) and low-pressure (LP; 100 PSI @ 15 to 20 GPM) water streams at variable flow rates through a single hose line and application nozzle.

DESCRIPTION: UHP and LP nozzle technologies already exist and are commercially available, although no one nozzle is capable of providing both UHP and LP water streams. A variable-pressure/flow-control nozzle will allow the first responder the option to utilize, as applicable, either technology to respond to fire incidents. The nozzle shall be designed to be compatible with the existing 4-stage centrifugal pump and 200 ft of 1-in high-pressure hose line mounted on the Air Force P-34 Rapid Intervention Vehicle (RIV).

The variable flow nozzle should be easily handled with similar design to existing firefighting nozzles i.e. with pistol grips and bails as needed to operate the nozzle. The ability to control the nozzle discharge in either UHP or LP shall be by a simple means of a nozzle bail or trigger and or combination of each for the discharge of water thorough the nozzle at variable flow rates. The application nozzle shall also be capable of straight and or fog patterns as selected by the operator.

Candidate technologies should balance commercial considerations with DoD requirements.

PHASE I: R&D goals of phase I are to identify the possibility of using a single pump, hose and nozzle system to provide both UHP and low-pressure waster flows between 15 and 20 GPM at variable pressures from 100 to 1500 PSI Phase I deliverable is design specifications. Offerors are encouraged to work with AFCEC's Fire Research Group during the design stage.

PHASE II: Produce a full-scale prototype nozzle. Provide detailed specifications of max and min pressure, GPM and capabilities of the nozzle. Conduct a full-scale demonstration of the nozzle at AFCEC's Fire Research Facilities

PHASE III DUAL USE APPLICATIONS: Deliver a marketable product with detailed installation/operator guidance manual.

REFERENCES:1. National Fire Protection Association (NFPA) Standardshttp://www.nfpa.org/codes-and-standards/all-codes-and-standards/list-of-codes-and-standards

2.http://www.dodfirenews.com/p-34.html

3.http://www.fireengineering.com/articles/print/volume-165/issue-11/features/ultra-high-pressure-firefighting-technology.html

4.http://www.afcec.af.mil/news/story.asp?id=123361014

KEYWORDS: Fire, Firefighting, Mist, Nozzle, Pressure, Stream, Water

AF171-002 TITLE: Wide-angle

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Retroreflectometer

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: A hand‐held system that fits light‐tight over reflective beads marking runway surfaces and measures light intensity reflected at angles from 0–45° from a beam incident at 0–45 degrees and displaced 0–30 degrees from the reflected beam.

DESCRIPTION: Retroreflective glass beads are widely employed as a technology for improving the visibility of highway road markings to drivers in unlighted areas at night. In the context of that application, two limiting geometries are regularly important: as the vehicle approaches a road sign or other horizontal marker, light arrives perpendicular to the reflective surface and returns along a nearly antiparallel optical path to the observer; at centerline striping and edge markings, light from the vehicle arrives nearly parallel to the road surface and reflects back to the driver at an angle that is only slightly larger. Technology for high‐precision measurement of perpendicular reflectance that operates in a range of ~0.5 degree from the normal is available and widely used to evaluate the condition (inferred from 90‐degree reflectance of light incident at ~90 degrees) of both categories of highway markings.

Until the adoption of centerline runway illumination, reflective glass beads were also the tool of choice to provide observability to allow pilots to land aircraft at night and taxiing. Their utility in for this purpose was effectively eliminated when runway lighting came into use, but use of the beads has been continued as a backup in the event of a lighting failure, and because they afford some measure of visibility on the ground, reflecting landing and taxiing lights. As for the second highway case, measurement with current technology is marginally representative at best because illumination and reflection for aircraft on runway and taxiway surfaces occur at geometries vastly different from that measured by conventional retroreflectometers, for which measured reflectances typically vary widely in field measurements.

The instrument sought will perform measurements of reflectance at geometries representative of aircraft operations, from which criteria indicating need for and that restriping treatments must pass for acceptance will be developed to replace the FAA recommendations based on perpendicular reflectance. The instrument sought will exclude external light and allow independent adjustment to the nearest degree of the incident angle, reflected angle, and radial displacement of the latter from the vertical plane of the former. It will operate on rechargeable batteries, preferably solar, for at least 4 hours, and onboard software will calculate means and standard deviations for sets of nine adjacent measurements defining a square array at each sampling point.

PHASE I: Develop a breadboard prototype. Demonstrate proof of concept in a darkened laboratory: reproducibly (+/- 20% for six sampling points in each angular dimension) map reflectance of a 1-inch square each of a commercial reflective tape and a runway coating to which highway beads have been applied to the supplier's specifications. Deliverables include a constructible design for a field-testable prototype.

PHASE II: Produce a full-scale prototype and mar, as in phase I, five randomly selected sites each on new and old coatings on asphalt and concrete highway surfaces and new and old coatings on asphalt and concrete runway surfaces. For each, agreement between averages of the prototype's and conventional instrument's measurements in perpendicular orientation must agree within 20%. Deliverables include a 50% design for a manufacturable prototype

PHASE III DUAL USE APPLICATIONS: Deliver a marketable product that minimally trained personnel deployed in an austere environment can operate. Unit will survive being dropped 4 feet onto a concrete surface and rolled down a 20-foot, 15% incline, and will function in rain or salt spray and at temperatures from -30 to 140 degrees F.

REFERENCES:1. Airfield Marking Handbook, Innovative Pavement Research Foundation Project 05-01 Report, available fromhttp://www.iprf.org/products/main.html

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2. "Retroreflection from spherical glass beads in highway pavement markings. 2. Diffuse reflection (a first approximation from calculation)." Vedam, K., and Stout, M.D., Applied Optics, (1978) 17(12):1859-1869.

3, Pavement Markings and Safety, Smadi, O.; Hawkins, N.; Nlenanya, I.; and Aldemir-Bektas, B., Iowa Highway Research Board Project TR 580, Nov 2010; available fromhttp://www.intrans.iastate.edu/reports/pvmt_markings_safety_report.pdf

KEYWORDS: Beads, markings, observability, reflectance, reflection, runway, taxiway, visibility

AF171-003 TITLE: Alternative Method of Surface Activation of High Strength Steels for Electroplating

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop a surface activation technology for electroplating landing gear parts that shall reduce the amount of material removed from the parts, improve plating adhesion, reduce waste, and lower risks to both personnel & landing gear parts.

DESCRIPTION: In the preparation of landing gear parts to be electroplated, the parts are usually prepared using a blasting technique. The blasting technique utilizes either aluminum oxide or garnet and this process is an aggressive technique which activates the surface. The activation is obtained by abrading off the surface layer by one ten-thousandth to one thousandth of an inch per second.

As material is abraded from the base material, some particulates of the base metal become part of the blast media. This cross contamination of the blast material creates possible problems such as corrosion of landing parts by dissimilar metals. In order to minimize the problems associated with cross contamination, independent blasting systems are used for each metal type. Additionally, the blast media is a non-renewable material and after cycling through the filtration system, the particles that are too small are discarded. These attributes increase the operational cost for preparing landing gear parts for electroplating.

The Air Force is interested in other methods for preparing the surface for electroplating. Because of the high dynamic stresses that landing gear undergoes, compatibility of the process must be such that the surface activation process does not over-heat the base metal (not to exceed 425 deg. F.), cause embrittlement of the base metal, or other danger to the landing gear. In addition, the removal of the base material while activating the surface should be minimal. It is preferred that only the first few atoms of the surface will be removed instead of up to a ten-thousandth of an inch.

The new technology needs to be able to function on multiple landing gear parts that consists of different high strength steel (heat treat = 180ksi) alloys in a variety of sizes and shapes. Conduct feasibility verification and validation testing of the alternative technology to include, but not limited to, adhesion of electroplated materials to base metal, temperature testing, fatigue testing, corrosion testing and hydrogen embrittlement testing. Along with the safety of the landing gear parts; personnel safety must be taken into consideration.

PHASE I: Develop a solution that meets above requirements and conduct preliminary business case analysis (BCA) to determine implementation costs, including a return-on-investment (ROI) calculation that compares anticipated savings to expected costs. Mishap avoidance shall not be included in cost calculations. Proof-of-concept prototype(s) shall be developed to demonstrate conformance to the requirements.

PHASE II: Optimize the developed solution. Perform testing on large diameter surface areas as well as small surface areas, both outer diameters and inner diameters. Prepare specification so the technology can be demonstrated verified and validated. Continue to refine the BCA to determine costs for implementation; BCA should include an

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ROI calculation that compares the anticipated savings to the expected costs.

PHASE III DUAL USE APPLICATIONS: Continue to verify the technology’s activation of high strength steels for electroplating. Perform cost benefit analysis. Implement the new technology. Expand workload across all electroplating platforms which may include other Air Force bases.

REFERENCES:1. “Surface treatment of metals using an atmospheric pressure plasma jet and their surface characteristics,” M.C. Kima, b, S.H. Yanga, J.-H. Boob, J.G. Hanb; Nano Surface Technology Team, Korea Institute of Industrial Technology, Cheonan 330-825, South Korea.

2. “Plasma jet treatment of five polymers at atmospheric pressure: surface modifications and the relevance for adhesion”; International Journal of Adhesion and Adhesives, Volume 24, Issue 2, April 2004, Pages 171-177 Michael Noeske, Jost Degenhardt, Silke Strudthoff, Uwe Lommatzsch.

3. MIL-STD-1504.

4. A-A-1722.

KEYWORDS: electroplating, surface activation, landing gear

AF171-004 TITLE: Electroplating 3D Printed Materials

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Research and develop an appropriate process to include specifications, equipment requirements, optimal applications and cost/benefit for metal plating 3D Fused Deposition Modeling (FDM) and Stereo Lithography (SLA) printed parts.

DESCRIPTION: Metal plating FDM parts with chromium, nickel or copper can greatly enhance strength, durability, surface hardness, and heat resistance. Industry has claimed that the metal plating thickness of a FDM or SLA part can be between 0.001 - 0.020 inches and can improve strength by a factor of 20. Open source web searches and inquiries to FDM and SLA equipment vendors indicate that the 3D part plating process is poorly defined and there is very little information available to specify or replicate the process. Additionally, the processes for plating complex 3D printed FDM and SLA parts is not well understood from a design perspective and internal areas may not be plated consistently or predictably.

The Air Force is interested in employing a metal plating technology of FDM and SLA printed parts in Depot maintenance processes. Examples of FDM and SLA material that may be metal plated are ABS, Nylon, Polycarbonate, Polypropylene, or ULTEM 9085. The new technology shall demonstrate the ability to metal plate on complex FDM and SLA parts. The prospective parts may include: casting molds, large metal press molds, parts with conductive surface requirements, tooling, fixtures, and increased size parts (larger than 3’x2’x3’) that are then plated and bonded together.

This effort shall provide opportunities for the Air Force to employ metal plating of FDM and SLA printed parts to enhance attributes of strength, durability, surface hardness, and heat resistance. Additionally, the efforts shall quantify material properties, structural integrity, process predictability and reproducibility. Furthermore, this effort shall develop process specifications and design guidelines. The efforts shall identify limitations, level of effort, space & utility requirements, equipment, and time requirements. Provide a business case analysis quantifying the expected cost for plating along with several alternative materials including part complexity and thickness of metal.

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Verify plating can be applied uniformly at any desired thickness range between 0.001 – 0.020 inches. Validate and verify plated prototype parts and evaluate the enhancements at varying plating thicknesses. The printed parts shall have bond lines where printed parts have been joined together. Validate finite element analysis for structure optimization.

PHASE I: Develop a solution that meets above requirements and conduct preliminary business case analysis (BCA) to determine implementation costs, including a return-on-investment (ROI) calculation that compares anticipated savings to expected costs. Proof-of-concept prototype(s) shall be developed to demonstrate conformance to the requirements.

PHASE II: Proof-of-concept prototype(s) shall be refined to installation-ready article and shall undergo testing to verify and validate all requirements. This process may require multiple iterations before a final design is selected. Refine BCA/ROI based on the final design.

PHASE III DUAL USE APPLICATIONS: If cost effective, implement developed technology.

REFERENCES:1. Stratasys Finishing Processes Bond, seal and beautify 3D printed partshttp://www.stratasys.com/solutions/finishing-processes/electroplating#sthash.Ngpp8nYf.dpuf.

2. CREATING COMPLEX HOLLOWMETAL GEOMETRIES USING ADDITIVE MANUFACTURING AND METAL PLATING, David Lee McCarthy; http://sffsymposium.engr.utexas.edu/Manuscripts/2012/2012-08-McCarthy.pdf

KEYWORDS: 3D printing, electroplating, strength

AF171-005 This topic has been deleted from this Announcement

AF171-006 TITLE: Development of Additive Manufacturing for Landing Gear Components

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Research and develop Additive Manufacturing (AM) technologies for landing gear components to enable testing and production of landing gear components using AM techniques.

DESCRIPTION: Due to the extreme operational loading and harsh environments, landing gear designs have led to manufacturing and fabrication processes that are lengthy (i.e. forgings) and expensive. Landing gear primary structural components include pistons, cylinders, truck beams, drag braces, side braces. Secondary components include actuators, links, gear boxes, brackets, bushings and bearings. Many components require forgings to ensure proper grain flow in order to prevent premature fatigue failures. The need for forgings adds significant costs, delays, and complexity to the manufacturing process. Additionally, current machining methods limit component designs to produce the most efficient geometry for strength and weight reduction. Many components are currently made from lower cost materials (low alloy steel and aluminum). Other alloys, such as titanium, could greatly improve the part performance, strength to weight ratio, weight, and corrosion resistance. In addition to the cost of materials for these high performance alloys, expense of manufacturing often offsets the feasibility of their use. In conjunction with material and fabrication challenges, USAF forecasting, planning, and procurement methods require purchasing of low quantity buys that eliminate economies of scale. This purchasing practice can inherently drive higher part costs,

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which is the case with costly forging and machining of landing gear components. With current landing gear manufacturing and fabrication processes, the cost to sustain the aging USAF fleet will continue to grow.

A game changing fabrication process is needed to replace current forging and machining processes to produce landing gear components of equal or improved strength, weight, and corrosion resistance. Metal additive manufacturing (AM, or 3D printing), technology has grown exponentially in the last several years and it appears now feasible to manufacture landing gear components using this technology. To achieve this, AM materials must be identified and tested to provide the required data that will satisfy USAF airworthiness requirements that will in turn, allow these materials to be used on current and future landing gear designs. Additionally, the required design processes, metal powder combinations, manufacturing techniques, post processing techniques, and qualification testing requirement must be developed for landing gear components.

Benefits to the use of AM technology for landing gear components include: cost savings, significant improvement in on-time deliveries of landing gear components, significant reduction in outside processing time, improved design alternatives, possibility for weight reduction, optimizing stress concentration areas, corrosion mitigation and improved production lead-time.

The purpose of this task is identification and development of AM material and process development for landing gear components. The task will investigate the following:

1. If a standard AM process is achievable for landing gear component materials and if the selected standard process will produce consistent repeatable mechanical properties as defined by industry standards

2. Design techniques/changes requisite for AM of landing gear components

3. Powder compositions for candidate materials including aluminum, titanium, steel and stainless steel alloys

4. AM techniques to ensure completed printed parts have the required material properties equivalent to existing material

5. Post processing requirements (Heat treatment, shot peening, High Velocity Oxygen Fuel (HVOF), plating (anodize, Low Hydrogen Embrittlement Zinc Nickel (LHE Zn-Ni), etc.)

6. Non-destructive Inspection/Test (NDI/NDT) and general testing methods to ascertain these techniques are robust to ensure part integrity

7. Qualification requirements

8. Equipment and facility requirements are identified and documented to ensure component integrity.

PHASE I: Research, develop & perform coupon level testing of candidate landing gear material. Phase I final report will provide results of how AM developed coupons compared with the traditional manufactured coupons & ability of the material to be viable for airworthiness certification of a candidate landing gear part.

PHASE II: Based on the Phase I research, work with the 417 SCMS government team to identify a candidate landing gear part for selection & AM fabrication, NDI/NDT evaluation, and Qualification Testing. The contractor shall complete a full-scale component fabrication & first article inspection. Following inspection the part shall be submitted to the required NDI/NDT processes for ver/val. After NDI/NDT the part shall be submitted to full qualification testing to ensure airworthiness compliance.

PHASE III DUAL USE APPLICATIONS: Based on the Phase I research, work with the 417 SCMS government team to identify a candidate landing gear part for selection & AM fabrication, NDI/NDT evaluation, and Qualification Testing. The contractor shall complete a full-scale component fabrication & first article inspection. Following inspection the part shall be submitted to the required NDI/NDT processes for ver/val. After NDI/NDT the

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part shall be submitted to full qualification testing to ensure airworthiness compliance.

REFERENCES:1. Additive manufacturing technologies rapid prototyping to direct digital manufacturing, By: Gibson, I., and D. W. Rosen.

2. http://www.ncms.org/wp-content/NCMS_files/AdditiveManufacturing/AddManMorning.pdf

3. http://www.asminternational.org/documents/17679604/17683439/White+paper.pdf/fba0eade-d6db-4921-b42f-668965d7c70a

KEYWORDS: Additive manufacturing, Landing Gear, Manufacturing, 3D printing, sustainment, high strength steel, materials science, high strength aluminum, titanium, aerospace structures

AF171-007 TITLE: Real-time, 3-D Model Deformation Measurement Capability for Perforated Wall Wind Tunnels

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop an accurate, real-time, 3-D capability for the quantitative measurements of position, attitude, and surface deformation of test models in large scale wind tunnels.

DESCRIPTION: Dynamic loading and deformation of wind tunnel models during testing contribute to the overall measurement uncertainty of aerodynamic parameters. Unlike flow-field uncertainties, which are quantified by wind tunnel calibration studies, the uncertainty associated with model attitudes and deformities has to be determined during the test. In the absence of a separate and calibrated diagnostic process, the effects produced by these irregularities of the model cannot be distinguished from the random error of the measured aerodynamic data. An innovative technology solution to accurately measure test article position, attitude, surface deformation and the quantification of fluctuations of these parameters is needed to meet test customer requirements.

Application of a measurement system of this nature is difficult due to test facility structure. To achieve air flow quality requirements, the AEDC 16T wind tunnel has porous walls in the test section that houses the test article and the overall porosity must not be significantly diminished. The optical and lighting components of this technology must be implemented without significant modifications to the porous wall design of AEDC’s 16T wind tunnel. The walls are ¾ inch thick and have many ¾ inch diameter holes drilled through them at a 60 degree angle with respect to the wall normal direction. The holes are spaced approximately 2.7 inches apart in a hexagonal pattern, described in reference 6. This pattern allows up to a 1.5 inch diameter hole to be drilled straight through the wall between any two canted perforation holes, and that straight hole can be used for optical access if necessary. This area of the tunnel sees pressures ranging from 47 to 4000 psf and temperatures from 60 to 140 degF. Any installed equipment would need to be able to withstand these conditions.

Innovative techniques to combine multiple images to produce highly accurate, real-time, 3-D test model position, attitude and surface deformation measurements during static and dynamic test events are needed. The ultimate goal is to develop a prototype system that can be transitioned to a wind tunnel test facility at AEDC, such as the 16T transonic wind tunnel. The prototype system should include optical components, data acquisition system, and software required to satisfy the topic.

PHASE I: Demonstrate feasibility of the technique to measure position, attitude and surface deformations of a representative 3-D model in a laboratory environment.

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PHASE II: Develop and demonstrate a prototype system that can make real-time, 3-D measurements of position, attitude, surface deformations and can quantify fluctuations of these parameters in a relevant operational wind tunnel environment.

PHASE III DUAL USE APPLICATIONS: Military Applications:  Applicable to subsonic, supersonic & hypersonic wind tunnels where position, attitude and/or surface deformation measurements are needed.Commercial Applications: Applicable to ground based testing of commercial flight vehicles to include aircraft & missiles.

REFERENCES:1. E. T. Schairer, et al., “Model Deformation Measurements of Sonic boom Models in the NASA Ames 9- by 7-Ft Supersonic Wind Tunnel,” AIAA Paper 2015-1913, 53rd AIAA Aerospace Sciences Meeting, January 5-9, 2015, Orlando FL.

2. Y. Le Sant, A. Durand, and M-C. Merienne, “Image Processing Tools Used for PSP and Model Deformation Measurements,” AIAA Paper 2005-5007, 35th AIAA Fluid Dynamics Conference and Exhibit, June 6-9, 2005, Toronto, Ontario, Canada.

3. J. S. Masters and K. E. Tatum, “Unstructured Mesh manipulation in Response to Surface Deformation, AIAA Journal, Vol. 54, pp 331-342 (2016).

4. T. W. Fahringer and B. S. Thurow, “3D Particle Position Reconstruction Accuracy in Plenoptic PIV,” AIAA Paper 2014-0398, 52nd AIAA Aerospace Sciences Meeting, January 13-17, 2014, National Harbor, MD.

5. B.C. Winkelmann, et al., “Application of Stereoscopic Imaging in Aerospace Ground Testing,” AIAA Paper 2014-2519, 30th AIAA Aerodynamic Measurement Technology and Ground Testing Conference, June 16-20, 2014, Atlanta, GA.

KEYWORDS: three-dimensional imaging, high-speed imaging, wind tunnel testing, transonic wind tunnels, test article attitude, surface deformation, 3-D test model position, dynamic loads, wind tunnel model position measurement, stereoscopic imaging

AF171-008 TITLE: Reduction/Elimination of Unsteady Aerodynamic Loads on Model and Balance Support Systems in Large Scale Wind Tunnels

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop a technology for effective damping or elimination of large oscillations in wind tunnel model balance support systems.

DESCRIPTION: Modern wind tunnel test articles involve models and balance support systems for force and moment measurements. Models are typically installed onto a compact internally mounted balance and supported by the sting at the other end. Models sizes can range between a small weapon such as a 5% scale 250 pound bomb to a 10% scale model aircraft ranging between 200 and 800 pounds. Loads on the larger models are limited to the balance capacity which can average around 3,000 lb of force, 10,000 in-lb of moment. Conditions in the wind tunnel are below 4,000 psf total pressure and less than 140 degrees F. Unsteady flow generated on models can result in vibration and oscillation of the model support system. Such motions, whether generated by the aerodynamics alone and/or in coupled with support system structure, result in contaminated data due to the unexpected motion of the model support system. Certain small to moderate unsteady data can be post processed to improve accuracy of such data. Under certain conditions a model may experience unexpected unsteady loads which exceed safe operational

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limits of the model support systems’ components. Such conditions, often due to the presence of oscillatory dynamics, may result in significant and expensive damage or loss of components and waste of valuable test time. An example includes rolling moment snaps from abrupt wing stall. Current vibration reduction and isolation techniques involve tuned vibration dampers, viscoelastic material, and active damping with piezoceramic material. While these techniques can provide favorable results in certain situations, their use is typically limited to specific models, configurations and test conditions.

The overall goal of this topic is to develop innovative and practical technology solutions to reduce/limit the amplitudes of oscillations experienced by a balance, using adaptive and or active control techniques. The proposed technology must be feasible for various model and balance support systems and effectively eliminate the potential for serious damage to the systems. It also must be easily adaptable to different model sizes, configurations and test conditions without extensive preparation and build up.

PHASE I: Demonstrate feasibility of an instrumented model support system for damping or eliminating large oscillations in a relevant laboratory environment.

PHASE II: Develop an interactive (adaptive and/or automated) prototype, including mechanical and control software and demonstrate the system in an AEDC large scale wind tunnel or other representative operational environment.

PHASE III DUAL USE APPLICATIONS: Military Applications:  This technology is applicable to wind tunnel testing of legacy and next generation air platforms.Commercial Applications: This technology is applicable to a large array of Commercial/University wind tunnel facilities across the U.S.

REFERENCES:1. Reduction of Wind Tunnel Model Vibration by Means of a Tuned Damped Vibration Absorber Installed in a Model; Igoe, W.B. and Capone, F.T.; NASA-TMX-1606, July 1968.

2. Passive and Active Damping Augmentation Systems in the Fields of Structural Dynamics and Acoustics; Freymann, R”; AIAA-1989-1196.

3. The Use of Friction Springs for Damping Model Vibrations; Fuykschot, P.H.; STA Proceedings, April 1999.

4. Active Damping of Sting Vibrations in Transonic Wind Tunnel Testing; S. Balakrishna, D. H. Butler, R. White, and W. A. Kilgore; AIAA- 2008-0840.

5. Design and Performance of an Active Damper for NASA Common Research Model; S. Balakrishna, D. H. Butler, Michael J. Acheson, & E. Richard White; AIAA-2011-953.

KEYWORDS: Model active dampening, passive dampening, force balance protection, sting dampening, model dynamics, unsteady loads, wind tunnel testing

AF171-009 TITLE: Miniature Video Camera Technology for Embedded Probes

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

OBJECTIVE: Development of a miniature video camera technology with the appropriate form factor and optical performance for embedding into small water-cooled probes for evaluating and monitoring turbine engine augmentor

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performance.

DESCRIPTION: AEDC develops and implements multi-purpose probes that are inserted into the hot, high speed, exhaust streams of turbine engines in order to measure pressure, temperature, velocity, species concentrations, and other performance characteristics. In particular, development of viewing probes have allowed unprecedented optical access to the turbine engine augmentors, but current needs far exceed the capability of available camera technologies. Camera technologies are unavailable that meet the requirements for size, form factor, optical quality and frame rates for embedding into probes used for augmentor performance evaluation, health monitoring and diagnosis. Spectral ranges have been limited to the visible, but short and long wavelength infrared images are needed, but not with a single camera technology.Camera technologies are required that meet the specifications in the table below:

Design Characteristics: Threshold(T), Objective(O), Stretch Goals(S)Number of pixels: 640 X 480(T), 1280 X 960(O), 2048 X 2048(S)Frame Rate: 30 fps interlaced(T), 100 fps non-interlaced(O), 1000 fps non-interlaced(S)Form factor: Cylindrical(T), Cylindrical(O), Cylindrical(S)Outer Diameter: 0.25 inches(T), 0.125 inches(O), 0.10 inches(S)Length: 1.65 inches(T), 1.0 inches(O), 0.875 inches(S)Spectral Range: Visible (T), Visible & near IR(O), Visible to LWIR(S)Performance Life (at relevant conditions): 1000 hours(T), 1500 hours(O), 2000 hours(S)

Innovative development techniques will be required to achieve the required form factor, size and camera performance. The innovative camera technologies will replace existing small diameter NTSC cameras. The camera technology must have automatic gain control and adjustable shutter speeds. Since the cameras will be embedded into probes inserted into the harsh environment of augmented engine exhaust flows, the camera must be rugged and robust (vibration insensitive for temperatures up to 195 ºF). Manual adjustments over shutter speeds and gains must also be available. The camera systems must have options for multiple lens with image steering capability up to 90 degrees.

PHASE I: Develop a proof-of-principal camera technology design capable of satisfying all objective requirements. A laboratory demonstration proving feasibility that the prototype components meet the vibrational and temperature requirements for extended periods of time (2 hours) is desirable.

PHASE II: Develop a prototype camera system satisfying all objective requirements and/or stretch goals and demonstrate camera performance life of 100 hours without failure in a relevant environment.

PHASE III DUAL USE APPLICATIONS: Formalize the production process and design the appropriate machinery/infrastructure to support full-scale commercial production. Military Applications: Monitoring of turbine engine augmentor operation. Gas turbine combustor monitoring. Rocket engine combustor monitoring. Video surveillance.Commercial Applications: Gas turbine combustor monitoring. Rocket engine combustor monitoring. Video surveillance.

REFERENCES:1. Hiers, R. S. Jr. and Hiers, R. S. III, “Development of High Temperature Image Probes for Viewing Turbine Engine Augmentors,” AIAA-2002-2912, 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, St. Louis, Missouri, 24 - 27 June 2002.

2. Hiers, R. S. III and Hiers, R. S. Jr., “Development of Exit-Plane Probes for Turbine Engine Condition Monitoring,” AIAA-2002-4304, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, Indiana, 7-10 July 2002.

3. Beitel, G. R., Jalbert, P. A., Plemmons, D., Hiers, R. S., and Catalano, D. R., “Development of Embedded Diagnostics for Internal Flow-Field Measurements in Gas Turbine Engines,” AIAA 2004-6865, AIAA/USAF

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Developmental Test & Evaluation Summit, Woodla

KEYWORDS: viewing probes, turbine engines, diagnostics, augmentors, miniature camera, Visible, LWIR

AF171-010 TITLE: Non-Intrusive, Time-Resolved Turbulence Measurements in Large-Scale Hypersonic Wind Tunnels

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop and validate a non-intrusive, time-resolved instrument for turbulence measurements in large hypersonic ground test facilities.

DESCRIPTION: The non-intrusive measurement of turbulence is a critical capability missing in Hypersonic T&E facilities. Such facilities can measure forces, moments, and surface quantities to support the validation of computations, but do not provide a complete understanding of the hypersonic flow physics needed to improve modeling. Moreover, the flow characterization of any wind tunnel involves knowledge of its freestream turbulence, which is composed of vorticity (incompressible turbulence), entropy (total temperature) and acoustic (tunnel noise) fluctuations. To date, the characterization of free stream fluctuations (tunnel noise) in large scale hypersonic wind tunnels has been limited to high frequency Pitot pressure measurements. Such measurements are performed behind a normal shock which distort the spectral content and the magnitude of the fluctuations as a function of the probe tip geometry (1). Recent boundary layer stability measurements and analysis performed at AEDC Tunnel 9 (2) have shown that 2nd mode transition can be predicted using Mack’s amplitude method. The accuracy of this method is dependent on the accuracy of the tunnel noise measurements at high frequencies.

A measurement technique that can discriminate between the disturbance modes (vorticity, entropy and acoustic) is highly desirable. Particle Image Velocimetry (PIV) and Laser Doppler Velocimetry (LDV) are thwarted by the high stagnation temperature of the flow and the impracticality of seeding the core flow. Approaches such as Rayleigh scattering (3), interferometry (4), and Schlieren methods (5) show promise, but have yet to be successfully applied for turbulence measurements in large scale hypersonic T&E facilities. The goal of this effort is to develop and demonstrate an instrument suitable for non-intrusive turbulence measurements in large-scale hypersonic wind tunnels. An instrument suite would also be acceptable, considering the multimodal nature of the freestream disturbances in hypersonic wind tunnels.

Typical test conditions for the USAF AEDC Hypervelocity Wind Tunnel 9 are: Mach number 8 to 14, run time 0.25 to 5 seconds, stagnation temperature up to 1850 K, static temperature 40 to 200 K, static pressure 3.5 to 10,000 Pa, static density 0.0003 to 0.56 kg/m3 , and velocity 1370 to 2070 m/s. Test section optical access is typically gained through two thick (50 mm) BK7 glass windows located 1.5 to 2 m apart, but smaller diameter (thinner) inserts with other optical materials can be implemented. The test gas is nitrogen. Hypersonic wind tunnel facilities produce low-frequency vibrations during testing which must be tolerated by the proposed instrument. Measurements should resolve turbulent frequencies up to 1 MHz to provide useful data for boundary layer transition. While this solicitation does not require “global” data, multiple point measurements are required to obtain turbulence length scale (without needing Taylor’s hypothesis) and convection velocity magnitudes and directions. Several (~20) simultaneous point measurements are needed without traversing the instrument, in order to characterize turbulence across a boundary layer in a single run. The measurement volume for each point should be less than 1 mm in size in all directions and the distance between measurement points should be as low as 1-mm. Finally, it is very important that the instrument be able to reject the sidewall boundary-layer located over the test cell windows.

PHASE I: Demonstrate the feasibility of a non-intrusive instrument for high-speed flow turbulence measurements, preferably in a small-scale supersonic or hypersonic wind tunnel or similar environment.

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PHASE II: Develop a non-intrusive, real-time turbulence prototype measurement system and demonstrate the prototype in large scale hypersonic wind tunnel.

PHASE III DUAL USE APPLICATIONS: The measurement technology can be marketed for non-intrusive turbulence measurements in high-speed wind tunnels and other high-speed flow applications.

REFERENCES:1. R. S. Chaudhry, G. V. Candler. Recovery of Freestream Acoustic Disturbances from Stagnation Pressure Spectrum in Hypersonic Flow, AIAA Paper 2016-2059.

2. E.C. Marineau, Prediction Methodology for 2nd Mode Dominated Boundary Layer Transition in Hypersonic Wind Tunnels, AIAA Paper 2016-0597.

3. A. F. Mielke, R. G. Seasholtz, K. A. Elam, J. Panda. Time-average measurement of velocity, density, temperature, and turbulence velocity fluctuations using Rayleigh and Mie scattering. Experiments in Fluids 39 (2): 441-454, 2005.

4. N. J. Parziale, J. E. Shepherd, H. G. Hornung. Free-stream density perturbations in a reflected-shock tunnel, Experiments in Fluids 55(2): 1-10, 2014.

5. S. Garg, G. S. Settles. Measurements of a supersonic turbulent boundary layer by focusing schlieren deflectometry, Experiments in Fluids 25 (3): 254-264, 1998.

KEYWORDS: turbulence, hypersonic, instrumentation, non-intrusive, seedless, wind-tunnel

AF171-011 TITLE: Advanced, Low-Erosion Electrode Technologies for Arcjet Testing

TECHNOLOGY AREA(S): Materials/Processes

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop advanced, cost-effective, arc-heater electrode materials and demonstrate significant reduction in erosion rates under typical operating conditions as compared to traditional electrode materials.

DESCRIPTION: Development of advanced hypersonic systems often requires arc-heater-based ground test facilities such as those at the AEDC, which can provide mission-representative high-enthalpy test environments. Development plans for the AEDC arc heater facilities call for expansion of the test environment envelope to broaden mission support, thereby placing considerably higher demands on arc heater subsystems and components, particularly the electrodes which deliver current to and from the high pressure air flow. The very high current density in the electrode arc attachment region, driven by both high arc currents and arc constriction associated with high pressure flow, inevitably causes erosion of electrode material, contaminating the flow and creating conditions conducive to arcing across insulator surfaces. Over the 35+ year history of AEDC arc heater operations, many

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improvements in electrode design, material selection, cooling techniques, etc., have been implemented to control flow contamination levels and maximize heater component reliability. However, the planned expansion of the test environment envelope will require increases in arc current, flow pressure, and run time, representing a significant increase in the severity of the electrode operating environment.

Individual arc heater runs, operating at thousands of amperes and up to 120 atmospheres of chamber pressure, can last up to several minutes. Because of this, the arc heater electrodes are nominally replaced after about 10 minutes of accumulated run time. Desired operating conditions include significant increases in run times, current, and pressure, which will significantly increase the severity of the thermal environment at the electrode-arc attachment region and likely reduce electrode lifetime to unacceptable levels. Forced electrode cooling and other mitigation measures have been optimized in terms of benefit to the arc attachment region, suggesting that new electrode materials, capable of handling higher current densities while retaining thermal and electrical conductivity similar to copper, be investigated as a possible remedy. Candidate materials/electrodes will be tested at typical arc heater operating conditions to evaluate ampacity, mass loss rate, and other performance parameters as compared to legacy materials/electrodes. After successful demonstration of improvement at typical operating conditions, candidate electrodes will be operated at higher currents, pressures, and run times to explore their expanded operational limits.

PHASE I: Research candidate composites and materials which lend themselves to production for use as electrodes and/or electrode liners. Produce test samples of selected materials and demonstrate ampacity and thermal/electrical conductivity which meet or exceed that of zirconium copper.

PHASE II: Develop prototype electrodes from candidate material(s) that meet/exceed specifications in description.  Dimensions of the electrodes used in the AEDC arc heaters do not exceed 8" in diameter and 6" in length. Demonstrate reduction in mass loss rate as compared to that of zirconium copper and the ability to survive the harsh environment in the AEDC Arc Heater H1 or H3.

PHASE III DUAL USE APPLICATIONS: Military Applications: Electrode Liners for AEDC's H1, H3, and MPAH (Mid Pressure Arc Heater), lighter electronics for any military device, possible EMP resistant devices.Commercial Applications: Electrical applications involving contacts/electrodes. Conductors in any small electrical device carrying relatively large currents.

REFERENCES:1. Subramaniam, Chandramouli, Takeo Yamada, Kazufumi Kobashi, Atsuko Sekiguchi, Don N. Futaba, Motoo Yumura, and Kenji Hata. "One Hundred Fold Increase in Current Carrying Capacity in a Carbon Nanotube–copper Composite." Nature Communications Nat Comms 4 (2013): n. pag. Web. 7 Mar. 2016. <http://www.nature.com/ncomms/2013/130723/ncomms3202/full/ncomms3202.html>.

2. Chu, Ke, Hong Guo, Chengchang Jia, Fazhang Yin, Ximin Zhang, Xuebing Liang, and Hui Chen. "Thermal Properties of Carbon Nanotube–Copper Composites for Thermal Management Applications." Nanoscale Research Letters. Springer, 9 Mar. 2010. Web. 16 Mar. 2016.

KEYWORDS: Carbon Nanotube-Copper Composite, CNT, High Current, Electrode, Arc Heater, Ampacity, Conductivity

AF171-012 TITLE: Air to Ground Target System for Engineering Based Airborne Electro-Optics Imaging System Performance

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of

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sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a ground based target system to enable measurement of sensitivity and spatial resolution of airborne target sensors with long range and full optical spectrum capability.

DESCRIPTION: The current state of existing engineering targets on the Edwards AFB precision impact range area (PIRA) would benefit greatly from innovative technology injection. Such upgrades would fulfill a number of current and future requirements while replacing existing limited capability at the end of its life. Research must be performed on how to implement the current requirements, perform system trade-studies, locating suitable system placement on the range, in addition to manufacturing, installing, protecting, sustaining, maintaining and quantifying the limitations, constraints and characteristics of the installed system. The resolution and sensitivity measurements of interest are modulation transfer function (MTF), relative edge response (RER), signal to noise ratio (SNR), noise equivalent delta temperature and (NEDT) noise equivalent delta radiance (NEDL) and any other objective measurements possible. The analysis tools for the metrics are in development (some already mature) by the 775TS/ENVD engineers, though a deeper understanding of optical remote sensing, radiometry, optical system imaging performance and resolution/sensitivity metrics is required for test setup and data analysis.

Requirements include a target system which allows measurement of sensitivity and resolution (preferable a knife edge). Capability to measure at long and short range, UV to LWIR (100nm to 12µm λ), color capability in the visible spectrum, highly uniform surfaces using the latest technology, fully instrumented for atmospherics, surface temperatures, radiance and turbulence (Cn2), built in protection from the elements, rotatable alignment for solar/lunar/flight path geometry, articulating for long range capability, maintenance schedule and procedures and system performance/limitations quantified.

If successful, this research, development, manufacturing and installation will not only provide a key test and analysis capability for efficient, consistent, repeatable, objective airborne electro-optics system imaging performance for any customer with aircraft optical sensors under test. In addition, the developer shall provide a training package for both 775TS/ENVD discipline engineers as well as Test Pilot School (TPS) students.

PHASE I: Research in this phase should focus on trade studies for realizing the requirements of the system in terms of hardware and software in addition to our 775TS/ENVD engineers gaining additional expertise in optical remote sensing, radiometry, optical system imaging performance, and more.

PHASE II: Research in Phase II should be focused on manufacturing, installation, protection, maintenance, and quantification of system performance of a pre-production prototype.

PHASE III DUAL USE APPLICATIONS: Military Application: This is an enabling target system technology with the potential to provide inputs for airborne electro-optical systems to quantify a number of sensitivity and spatial resolution metrics for test and evaluation of airborne electro-optics systems under test.  It will also be useful as a training tool for engineers and test pilots.Commercial Application: Research will be equally useful for any airborne or spaceborne electro-optics system.

REFERENCES:1.  C. Liebmann and M. Bennett, “Electro-Optic System Imaging Performance Developmental Test and Analysis Techniques Test and Evaluation (Have Light)”, USAFTPS-TIM-15B-01, 2016

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2.  G. Boreman, “Modulation Transfer Function in Optical and Electro-optical Systems”, ISBN-13: 978-0819441430, SPIE-The International Society for Optical Engineering, 2001

3.  J Silny and L Zellinger, “Radiometric Sensitivity Contrast Metrics for Hyperspectral Remote Sensors”, SPIE-The International Society for Optical Engineering, 2016

KEYWORDS: Airborne, Electro-optics, Infrared, Targets, Modulation Transfer Function, Relative Edge Response, Noise Equivalent Delta Temperature, Noise Equivalent Delta Radiance

AF171-013 TITLE: Next Gen Infrared Emitter Array Packaging

TECHNOLOGY AREA(S): Weapons

OBJECTIVE: Develop a robust, scalable packaging and cooling solution for next generation infrared emitter arrays.

DESCRIPTION: This SBIR topic seeks to explore alternatives for addressing technical challenges in developing a robust, scalable packaging solution for next generation infrared emitter arrays. Advanced arrays will introduce new challenges including interfacing high speed drive electronics to the array through the packaging and removing excess heat from the emitter surface of light emitting diode arrays which are orders of magnitude more sensitive to temperature variations than current resistive arrays. Also, due to their high pixel counts and relatively low efficiency, significantly more power must be provided through the package and subsequent generated heat removed. The packaging approach must be scalable to support arrays ranging from 1024 x 1024 (1K x 1K) pixels at 24 um and 48 um pixel pitch (i.e. ~1” and ~2” square arrays) up to 4K x 4K arrays at 24 um pixel pitch (~ 4” square array). The design must have physical characteristics (size, mass, robustness) to support multiple applications including mounting on dynamic flight motion simulators, cryogenic sensor testing, installed systems test facilities, and system integration labs.

The ability to stimulate advanced infrared weapon and aircraft sensors and seekers with high radiance, high resolution IR imagery of targets, backgrounds, and countermeasures in dynamic hardware-in-the-loop simulation (HITL) and installed systems test facilities (ISTF) is critical in the development, test, and evaluation of those systems. Current IR scene projectors are based on resistive emitter array technology that is approaching physical limits on radiance output, size, frame rates, and pixel density and will likely not provide adequate support for future test and evaluation (T&E) requirements. The current emitter array packaging, originally developed for cryogenic operation, supports 512x512 and 1024x1024 resistive arrays and has proven to be very robust but it is not scalable or suitable to support next generation IR emitter arrays.

Infrared sensor and systems are continually increasing in resolution and capabilities resulting similar increases in T&E requirements. Next generation IR emitter arrays are required to provide higher resolutions, higher radiance output (apparent temperature), and higher frame rates to test these systems. Current generation emitters provide a maximum frame size of 1024x1024 pixels, midwave infrared (MWIR) apparent temperatures of ~600K, 11 bits effective dynamic range, and ~200 Hz frame rates. Active efforts are underway to increase emitter resolution to a minimum of 2048x2048 pixels with an objective of 4096x4096, increase MWIR apparent temperature to 1300K - 3000K, improve dynamic range to 16 bits, and provide frame rates of 1000Hz. This will create challenges for the packaging solution to provide cooling, power, and data to the emitter chips.

It will also not be a one-size fits all requirement - different applications will required emitter arrays of different characteristics, sizes, and possibly different technologies requiring a flexible and scalable solution. Current research and development in IR emitter arrays include both advanced resistive arrays and infrared light emitting diode (LED) arrays. Techniques being investigated to increase resolution (i.e. pixel count) include reducing pixel pitch on monolithic arrays and tiling multiple arrays.

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A common, flexible, scalable, and verified packaging concept is required to support continued development and use of advanced emitter arrays. The package design must have provisions for cooling the emitter array, keeping the array under vacuum, and providing power and command/control signals to the array.

PHASE I: Identify key requirements for next gen IR emitter array packaging, develop and evaluate conceptual designs, determine technical feasibility of concepts, and design a follow on development and test program for the most promising concept.  Required deliverables will include reports and briefings documenting the designs and analysis.

PHASE II: Complete design and fabricate prototype array packages using the most promising concepts developed in Phase I.  Evaluate performance of the packages in a relevant environment.  Required deliverables will include reports and briefings on the results of the experiments.

PHASE III DUAL USE APPLICATIONS: Military Applications:  DT&E of IR guided weapons, threat warning and aircraft self-protection systems, electro-optical sensors.  Commercial Applications:  DT&E of IR sensors and systems including autonomous guidance, vision, and collision avoidance systems.

REFERENCES:1. Norton, Dennis, et al., "Development of high-definition IR LED scene projector." Proc. SPIE 9820, Infrared Imaging Systems: Design, Analysis, Modeling, and Testing XXVII, 98200X, 3 May 2016.

2. Norton, Dennis Thomas Jr. "Type-II InAs/GaSb superlattice LEDs: applications for infrared scene projector systems." PhD thesis, University of Iowa, 2013.

3. Lange, Corey Wyatt. "Design and Development of 512 512 Infrared Emitter Array System." Master's thesis, University of Delaware, 2011.

4. Franks, Greg, et al. "Development of an Ultra-High Temperature Infrared Scene Projector at Santa Barbara Infrared Inc." Proc. SPIE 9452, Infrared Imaging Systems:  Design, Analysis, Modeling, and Testing XXVI, 94520W, 12 May 2015.

5. James, Jay, et al, "OASIS: Cryogenically-Optimized Resistive Array & IRSP Subsystems for Space-Background IR Simulation." Proc. SPIE 6544, Technologies for Synthetic Environments:  Hardware-in-the-Loop Testing XII, 654405,24 Apr 2007.

KEYWORDS: Extraction, efficiency, Light, emitting, diode, LED, infrared, emitter, array, mid-wave, MWIR, long-wave, LWIR, hardware-in-the-loop, HITL, resistive, array, scene, projector, IRSP, Optoelectronics, tiling, quilting, scalable, cryogenic, electronics, pack

AF171-014 TITLE: Dynamic Aircraft Tire Footprint Sensor (DATFS)

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop a dynamic aircraft tire measurement system capable of tire footprint property measurement; integrated with internal drum dynamometer. Support aircraft loads and speeds with continuous measurements of all types of tire footprint properties.

DESCRIPTION: In military/commercial aircraft tires, tire tread life and stopping performance are greatly dependent on the tire dynamic contact surface profile. While the tire is rotating, portions of the tire profile will be slipping while other parts will be rolling in relation to the contact surface. Thus, the measurement of slip velocities during

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this process can create a large insight into tire life issues and improving antilock braking performance. Additionally, the added ability to capture and characterize contact stresses between the tire runway interface contract region, at a given angular position, may support performance/service life improvements and tire re-designs to improve tire life and improve tire responses during antilock braking. These improvements would significantly affect the large costs of poor performing tires and potentially improve stopping performance, which is always a critical safety-of-flight (SOF) concern.

Current T&E tire test machine envisioned for this effort is the 96th Test Group’s Landing Gear Test Facility (LGTF) 168-inch internal drum dynamometer (168i). This machine can apply a vertical force up to 150,000 lbs with camber (±10 degrees) and yaw (±20 degrees) for tests up to 350 mph. The machine is fully dynamic and can simulate all aspects of actual aircraft missions including touchdown, high-speed braking, takeoff, etc. There are currently no existing measurement methods to determine tire profile contact forces and slip velocities at high aircraft-related speeds. Therefore, a new measurement technology is required to obtain all pertinent information at the interface contact region between the tire and surface. Different surfaces have been installed and used on the 168i (including concrete runway), thus there would be space (appx 3 in thick and 2.5 feet wide) to retrofit an assembly to measure the contact forces. Additionally, there are also possibilities of developing a standalone unit for this system. This unit, however, would need to show it can hold a tire and subject the tire to controlled load, speeds, and other aspects that an internal drum dynamometer is capable of.

The new measurement system should be designed to provide real-time, continuous measurement of contact stress variations (both the normal and shear forces at the tire-runway interface), slip velocity, and footprint properties for high-speed (350 mph) dynamic tire tests while at loads up to 150,000 lbs. To minimize error and improve the accuracy and fidelity of current technology, the measurement system should introduce minimal test article interference. This measurement system must be capable of accurate and precise operation. The goal is to continually measure all of this information for a variety of dynamic simulated landing missions with speeds up to 250 mph. The system should be able of testing tires up to 60” in diameter, and 30” in width.

No other commercially-available system provides these capabilities. There have been systems developed for static, or quasi-static testing. However, to date there is no technology that acquires these high-speed slip, tire footprint, and shear stress measurements. The Air Force envisions four levels of success in the program.

PHASE I: Demonstrate feasibility of DATFS with minimal test article interference to determine all pertinent dynamic tire footprint properties listed above.  Explore tradeoffs relating to measurement area, spatial resolution, sensitivity, and dynamic response. The dynamic response will be key, due to the inherent hysteretic properties of some materials.

PHASE II: Develop full-scale demonstrator of DATFS that is applicable to aircraft tire loads and operating environment.  Demonstrate sensor test repeatability with less than 5% error.  Demonstrate automated data acquisition with data able to be imported into finite element models.  Demonstrate capability to the sensor results and how the tire footprint properties are changing with different test conditions.  Deliver final prototype sensor to 96 TG LGTF and demonstrate potential with 168i or similar.

PHASE III DUAL USE APPLICATIONS: Military applications: Develop final sensor.  Show utilization of data for tire life and antiskid.  Commercial applications:  A test system for airlines, automotive, truck, and heavy equipment and test facilities.  Original equipment manufacturers (OEMs) expressed interest to assist tire life and potential antilock improvements.

REFERENCES:1. Crane, D.  "Aircraft Tires and Tubes," Second Edition, an Aviation Maintenance Publishers, Inc.  Training Manual, EA-ATT-2, 1980.

2. Castillo, J., Blanca, A. Prez De la, Cabrera, J. A., Simm, A. An optical tire contact pressure test bench, Vehicle System Dynamics, 44 (3): pp. 207-221(15), 2006

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3. Fonov, S., Jones, G., Crafton, J., Fonov, V., Goss, L.  The development of optical techniques for the measurement of pressure and skin friction, Measurement Science and Technology, 16: pp. 1-8, 2005.

4. McClain, J.G., Vogel, M., Pryor D. R., Heyns, H.E.  The United Air Force Landing Gear Systems Center of Excellence A Unique Capability, AIAA, 2007-1638.

5. Zakrajsek, Andrew J., Childress, Jonathan M., Bohn, Michael H., et al.  "Aircraft Tire Spin-Up Wear Analysis through Experimental Testing and Computational Modeling."  57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference.

KEYWORDS: Dynamic Slip Velocities in Tires, Tire Contact Profile, Tire Life, Tire Wear, Dynamic Testing, Aircraft Tire, Footprint Properties, Normal and Shear Contact Interface Pressure, Dynamic Interface Pressure, Flight Line, Aircraft, Maintenance Checks, Cost Re

AF171-015 TITLE: Infrared Light Emitting Diode Extraction Efficiency

TECHNOLOGY AREA(S): Weapons

OBJECTIVE: Develop technologies to improve extraction efficiency of high density infrared light emitting diode arrays to improve radiance output, self-heating, and wall-plug efficiency.

DESCRIPTION: This SBIR topic seeks to identify and demonstrate technologies that can improve the light extraction efficiency of high density mid-wave infrared (MWIR) and long wave infrared (LWIR) light emitting diode (LED) arrays designed to be used in infrared (IR) scene projectors without affecting the ability to control the radiance on a per-pixel level. The enhancements must be applicable for incorporation into projector systems suitable for use in hardware-in-the-loop (HITL) simulation and Installed System Test Facility (ISTF) applications.

The ability to stimulate advanced infrared weapon and aircraft sensors and seekers with high radiance, high resolution IR imagery of targets, backgrounds, and countermeasures in dynamic hardware-in-the-loop simulation and installed systems test facilities is critical in the development, test, and evaluation of those systems. Current IR scene projectors are based on resistive emitter array technology that has numerous limitations including output radiance, frame rates, and frame size.

Infrared (IR) LED arrays have shown great potential for application to advanced IR scene projectors. LED arrays may improve radiance levels, operating speed, and frame size over other existing technologies. Developmental LED arrays range from 512x512 pixels on a 48 micron pixel pitch (~1 inch square array) to 2048x2048 arrays on a 24 micron pitch (~2 inch square array) with potential growth to larger arrays. The LED arrays are driven by a read-in integrated circuit (RIIC) which provides control of the radiance output of each pixel based on the desired IR image from a scene generation system and the ability to provide non-uniformity correction across the array. A significant issue with current generation IR LED arrays is the light extraction efficiency (LEE) which is typically less than 1%. Even slight improvements to the LEE would greatly increase maximum radiance, reduce waste heat which must be removed from the arrays, and increase wall-plug efficiency. An example is a 512x512 superlattice LED array with about 1% extraction efficiency where each pixel at full power consumes 15 milliamps at 12 volts. If all quarter million pixels were turned on, the one inch square array would be required to dissipate 47 kW.

The low efficiency significantly impairs the utility of the LED arrays. Not only does the reduced radiance limit the types of imagery that can be projected, a very large amount of waste heat is generated that, even with extensive cooling, can affect operation of the array and even permanently damage the devices.

PHASE I: Identify factors that limit extraction efficiency, define concepts that may increase the efficiency, determine the technical feasibility of the concepts, and design a follow-on test program for the most promising

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concepts.  Required deliverables will include reports and briefings documenting the analysis and the results

PHASE II: Complete design and fabricate small prototype IR LED arrays using the most promising concepts developed in Phase I.  Perform characterization experiments quantifying the effects on extraction efficiency and on overall LED performance including output radiance, self-heating, and wall-plug efficiency.  Required deliverables will include reports and briefings on the results of the experiments.

PHASE III DUAL USE APPLICATIONS: Military Applications:  DT&E of IR guided weapons, threat warning and aircraft self-protection systems, electro-optical sensors.  Commercial Applications:  DT&E of IR sensors and systems including autonomous guidance, vision, and collision avoidance systems.

REFERENCES:1. Norton, Dennis Thomas Jr.  "Type-II InAs/GaSB superlattice LEDs:  applications for infrared scene projector systems."  PhD thesis, University of Iowa, 2013.

2. Norton, Dennis, et al., "Development of a high-definition IR LED scene projector."  Proc.  SPIE 9820, Infrared Imaging Systems:  Design, Analysis, Modeling, Testing XXVII, 98200X, 3 May 2016.

3. Lange, Corey Wyatt.  "Design and Development of 512 512 Infrared Emitter Array System." Master's thesis, University of Delaware, 2011.

KEYWORDS: Extraction, efficiency, Light, emitting, diode, LED, infrared, emitter, array, mid-wave, MWIR, long-wave, LWIR, hardware-in-the-loop, HITL, scene, projector, IRSP, Optoelectronics.

AF171-016 TITLE: Efficient On-Board Fire Suppression

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Efficiently and economically suppress on-board aircraft fires using a non-toxic and non-corrosive agent while balancing cost/logistics burdens.

DESCRIPTION: Halon is a highly effective fire suppression agent that remains in-use on many legacy military vehicles. In 1987, Halon production phased out with signature of the Montreal Protocol (an international treaty banning further production of such ozone-depleting substances). Since then, a search for equally effective agents has been on-going. Alternative solutions have proven less capable and often with burdens of higher cost, volume, and weight; greater toxicity and corrosiveness; and greater or unique logistics challenges. The present SBIR topic takes a renewed search for novel solutions first by concentrating on designing, producing, and demonstrating effectiveness of a fire suppression agent that is environmentally safe and has few logistics challenges. Effectiveness is judged based on the least amount of agent weight/volume to extinguish a given fire. Goal is to obtain effectiveness on par with Halon. The present SBIR then continues by marrying the proposed agent to an on-board fire suppression system. Teaming with (or consulting with) an aircraft manufacturer is encouraged to ensure aircraft suitability.

The proposed agent must be non-toxic, non-corrosive, non-ozone-depleting, and highly effective at lowest possible weight/volume. The agent should be simply formulated without specialized handling requirements (pressurization, cooling, or heating) when in shipment or storage to avoid cost and logistics burdens. When integrated into a fire suppression system, the agent must remain viable for long periods of time (not less than a year) even when exposed to extreme flight-line temperature swings and in-flight conditions, must be compatible with the proposed fire suppression system concept, and must be fully effective against aircraft fuel fire applications. The fire suppression system must be capable of aircraft integration at the lowest possible cost/weight/volume and must be capable of transmitting agent to the fire zone in a timely/efficient manner (ideally without need for total bay flooding). The

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aircraft-suitable fire suppression system should have the following attributes: low/no clean-up requirements after agent discharge; long life; non-clogging/non-clumping; and low maintenance. For active systems, the goal is to achieve fire suppression within 100ms of fire detection while using the smallest weight/volume of agent. For passive systems, the goal is to achieve fire suppression within 100ms of suppressant discharge while using the smallest weight/volume of agent.

PHASE I: Prepare an efficient and economical fire suppression system design concept that incorporates an effective environmentally-safe agent having few cost/logistics burdens.

PHASE II: Design, produce, and demonstrate effectiveness of the proposed environmentally-safe fire suppression agent.  Couple the agent with a complete fire suppression system to demonstrate overall system effectiveness at costs, weights, and volumes lower than conventional Halon systems.

PHASE III DUAL USE APPLICATIONS: Military Applications:  Aircraft, ground vehicle, ship, submarine, and building fire suppression.  Commercial Applications:  Transportation industry (aircraft and ground vehicle fire suppression); residential and commercial building fire suppression.

REFERENCES:1. Gann, R.G., "Screening Tests for Alternative Suppressants for In-Flight Aircraft Fires", The weekly of Business Aviation, Issue 4, Vol. 100, 2 Feb 2015

2. McMillin, M., "Consortium Seeks Halon Alternatives for Aircraft Propulsion Systems", Overhaul & Maintenance, Issue 3, Vol. 12, 1 Mar 2006

3. Gann, R.G., "Guidance for Advanced Fire Suppression in Aircraft", 1st Conference on Fire Suppression and Detection Research and Applications, Vol. 44, Issue 3, Sep 2008.

KEYWORDS: Efficient, effective, environmental, safe, aircraft, fire, suppression, extinguishing, agent, system, low, cost, weight, volume, logistics.

AF171-017 TITLE: Low Cost High Sensitivity Superconducting Magnetometers and Gradiometers

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

OBJECTIVE: Develop low cost, high sensitivity magnetometers and gradiometers utilizing direct-write, high-transition-temperature superconducting nano-Josephson junction SQUIDs.

DESCRIPTION: There are a number of potential applications involving detection of small magnetic fields (< 1 pT) that are relevant to the DoD, such as non-destructive evaluation of aging aircraft and biomagnetic measurements of the human body [1]. Using an essentially portable HTS SQUID system whose temperature would operate in the vicinity of liquid nitrogen temperature, it is conceivable that such a system can be utilized to evaluate the state of health of each pilot and other crew members noninvasively, and it could make this evaluation in a period of less than 10 minutes. Superconducting quantum interference devices (SQUIDs) provide unmatched performance in terms of bandwidth, sensitivity and dynamic range [1]. Unfortunately, SQUIDs comprised of conventional superconducting materials require cooling to about 4 degrees kelvin, employing liquid helium or large costly power-hungry and noisy refrigeration. SQUIDs comprised of ceramic high temperature superconducting (HTS) materials could alleviate the size, weight and power (SWaP) requirements by two orders of magnitude in comparison to the bulky and generally non-portable SQUID magnetic gradiometer systems [2]. Such traditional SQUID systems have been the norm thus far. However, until now it had not been possible to employ these more recent ceramic superconducting materials, as they had been found to be very difficult to work with, namely because of anisotropic electrical properties and

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intrinsic noise [3]. Despite these problems, there have been some demonstrations [4] of suitable low-noise HTS SQUIDs with acceptable noise properties. Historically, the reproducibility and circuit yield have been very low, thus making the cost per SQUID sensor prohibitive for practical applications.

Recently Cybart et al. [5] have demonstrated a new direct-write approach for fabrication of HTS SQUIDs using helium ion-beam lithography, solving many of the problems associated with HTS SQUIDs such as reproducibility, circuit yield and cost. This demonstration provided a reliable method for fabrication of low-noise SQUIDs, but greater sensitivity is needed which requires a flux concentrator. In this program, a handheld SQUID prototype sensor composed of a helium ion direct write SQUID and suitable flux concentrator will be constructed for detection of magnetic fields smaller than 1 pT over a bandwidth from 0.1 Hz to 1 MHz.

PHASE I: Simulate and design high Tc SQUID magnetometer and gradiometer sensors using helium ion direct-write Josephson junctions that will function at temperatures near 77 K. The circuits should be composed of both a helium ion beam HTS SQUID and a flux concentrator which will substantially increase sensitivity. Designs comprising both planar washer type direct-inject and multilayer SQUID input coils will be considered and evaluated.

PHASE II: Handheld prototype magnetometers and gradiometers using the designs developed in phase I will be constructed. These sensors will be characterized in a flux-locked loop to determine their sensitivity, bandwidth and dynamic range. Devices will be operated in a micro-dewar and/or on compact cryocoolers to determine practical size and weight requirements, noise properties and other capabilities.

PHASE III DUAL USE APPLICATIONS: Produce and market magnetometers and gradiometers for biomedical and non-destructive evaluation instrumentation. This phase would result in the introduction of this technology to real applications.

REFERENCES:1. H. Weinstock, “SQUID Sensors: fundamentals, fabrication, and applications”, Springer, 1996.

2. H. J. M. Ter Brake, G. F. M. Wiegerinck, Cryogenics, 42, p 705, 2002.

3. D. Koelle, R. Kleiner, F. Ludwig, E. Dansker and J. Clarke, Rev. Mod,. Phys. 71, p 631 1999.

4. M. Faley, et al. IEEE Trans. Appl. Supercond. 23, p 1600705 2013.

5. S. A. Cybart, et al. Nat. Nanotechnol. 10 p 598, 2015.

KEYWORDS: SQUID, nondestructive evaluation, magnetometer, magnetic gradiometer, HTS superconductor

AF171-018 TITLE: Gallium Oxide Homo/Hetero-Epitaxial Structures for RF and Power Switching Devices

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors

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are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop and demonstrate Beta-Gallium Oxide (ß-Ga2O3) epitaxial structures suitable for fabrication of Metal Oxide Semiconductor Field Effect Transistor (MOSFET) and High Electron Mobility Transistor (HEMT) devices.

DESCRIPTION: Next generation Air Force sensing systems depend on continued electronic materials innovation leading to enabling performance capabilities. Interest in ß-Ga2O3 has grown recently due to its unique combination of a large bandgap (4.8eV), estimated breakdown field (8 MV/cm), high electron mobility and availability of native single crystal substrates using inexpensive melt-based growth methods [1-5]. ß-Ga2O3 possesses a larger bandgap, higher breakdown voltage and lower on-resistance than those of Silicon Carbide (SiC) and Gallium Nitride (GaN). Exploitation of ß-Ga2O3 semiconductors holds promise for revolutionary improvements in the cost, size, weight and performance of a broad range of radio frequency, power switching and opto-electronic components utilized in radar, electronic warfare and communication systems. The realization of devices with optimal performance will require controlled growth of doped, high quality, homo/hetero-epitaxial structures on ß-Ga2O3 substrates. Common approaches under consideration for homo/hetero-epitaxial film growth include Molecular Beam Epitaxy (MBE), Metal-Organic Chemical Vapor Deposition (MOCVD), Metal-Organic Vapor-Phase Epitaxy (MOVPE) and Halide Vapor-Phase Epitaxy (HVPE). Homo-epitaxial, doped ß-Ga2O3 films can be grown enabling fabrication of MOSFET devices. Growth of hetero-epitaxial structures such as (AlxGa1-x)2O3/ Ga2O3 or (InxGa1-x)2O3/ Ga2O3 support fabrication of HEMT devices [6]. There is a need for a viable US-based source to develop and scale ß-Ga2O3 epitaxial processes to underpin and help drive the development of next generation ultra-high performance devices.

PHASE I: Develop growth parameters for; (i) homo-epitaxial growth of MOSFET structure comprised of doped Ga2O3 films on bulk semi-insulating ß-Ga2O3 substrates and (ii) hetero-epitaxial growth of HEMT structure comprised of doped (AlxGa1-x)2O3/ Ga2O3 or (InxGa1-x)2O3/ Ga2O3 films on bulk (010) semi-insulating ß-Ga2O3 substrates. Deliver epitaxial wafers for Government evaluation.

PHASE II: Demonstrate; (i) homo-epitaxial growth of MOSFET structure comprised of doped Ga2O3 films on bulk (010) 50mm semi-insulating ß-Ga2O3 substrates and (ii) hetero-epitaxial growth of HEMT structure comprised of doped (AlxGa1-x)2O3/ Ga2O3 or (InxGa1-x)2O3/ Ga2O3 films on bulk (010) 50mm semi-insulating ß-Ga2O3 substrates with nm-scale thickness uniformity at sub-nm RMS roughness levels. Characterize the epitaxial properties and modify the structure accordingly to enhance device performance.

PHASE III DUAL USE APPLICATIONS: Phase III shall address the commercialization of the product developed as a prototype in Phase II. Commercialize device-quality homo/hetero-epitaxial layers to device partners.

REFERENCES:1. M. Higashiwaki, K. Sasaki, A. Kuramata, T. Masui, and S. Yamakoshi, "Gallium oxide (Ga2O3) metal-semiconductor field-effect transistors on single-crystal beta-Ga2O3 (010) substrates," Applied Physics Letters, vol. 100, Jan 2 2012.

2. M. Higashiwaki, K. Sasaki, T. Kamimura, M. H. Wong, D. Krishnamurthy, A. Kuramata, et al., "Depletion-mode Ga2O3 metal-oxide-semiconductor field-effect transistors on beta-Ga2O3 (010) substrates and temperature dependence of their device characteristics," Applied Physics Letters, vol. 103, Sep 16 2013.

3. W. S. Hwang, A. Verma, H. Peelaers, V. Protasenko, S. Rouvimov, H. Xing, et al., "High-voltage field effect transistors with wide-bandgap beta-Ga2O3 nanomembranes," Applied Physics Letters, vol. 104, Jun 16 2014.

4. K. Sasaki, A. Kuramata, T. Masui, E. G. Villora, K. Shimamura, and S. Yamakoshi, "Device-Quality beta-Ga2O3 Epitaxial Films Fabricated by Ozone Molecular Beam Epitaxy," Applied Physics Express, vol. 5, Mar 2012.

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5. K. Sasaki, M. Higashiwaki, A. Kuramata, T. Masui, and S. Yamakoshi, "Ga2O3 Schottky Barrier Diodes Fabricated by Using Single-Crystal beta-Ga2O3 (010) Substrates," Ieee Electron Device Letters, vol. 34, pp. 493-495, Apr 2013.

6. R. Wakabayashi, K. Sasaki, A. Ohtomo, et al., Growth and electric properties of conductive ß-(AlxGa1-x)2O3 films, 1st International Workshop on Gallium Oxide and Related Materials, November 3-6, 2015.

KEYWORDS: Gallium Oxide, epitaxy, wide bandgap semiconductor

AF171-019 TITLE: High-Speed Wind Tunnel Transient Dynamics During Start-up

TECHNOLOGY AREA(S): Air Platform

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Mitigate risk to high speed aerospace ground test facilities and test articles during wind tunnel startup.

DESCRIPTION: During the start and unstart of high-speed wind tunnels, a model may experience a transient airload that is several times greater than the steady load, placing undesired forces and moments on the model, support structure, and balance measurement system. A similar problem exists in the start and unstart of ramjet and scramjet inlet models which are of increasing importance in the development of advanced flight systems.

Conduct Computational Fluid Dynamics (CFD) and structural analysis and small scale supersonic/hypersonic wind tunnel experiments to determine the forces and moments that are transmitted to test articles when injected into supersonic / hypersonic flow paths (i.e., similar to the Arnold Engineering Development Complex [AEDC] VKF tunnel model injection scenario). Compare these results to the loads that a test article would experience if left in place during the wind tunnel start-up process (i.e., no model injection and the test article sees the full start up shock). The test and analytical efforts should use the same test article geometry. The CFD should be time-accurate (LES turbulence modeling is desired) to fully account for the wind tunnel transient dynamics during startup. All work to be monitored by Subject Matter Experts.

Phase 1 will develop a software application that, given specific test geometry, will provide an accurate assessment of airloads on a test article as it is injected into the airstream of a ground test facility and during startup for wind tunnels without model injection capability. This development will continue during Phase 2 and proposers will conduct air flow testing in wind tunnel(s) to validate the software model. Proposers MUST demonstrate that their team has the capability to obtain wind tunnel validation data safely and discuss the team’s qualifications and experience for this in ALL proposals. At the end of Phase 2, software will be installed and demonstrated at an Air Force facility. Deliver software, source code, documentation, and data.

PHASE I: Develop software application that, given specific test geometry, will provide an accurate assessment of airloads on a test article as it is injected into the airstream of a ground test facility and during startup for wind tunnels without model injection capability.

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PHASE II: Conduct air flow testing in wind tunnel(s) to validate the software model. Install and demonstrate at Air Force facility. Deliver software, source code, documentation, and data.

PHASE III DUAL USE APPLICATIONS: Software will be of interest to other DoD and government test sites, including NASA. Manufacturer of DoD and commercial aircraft are potential customers for transition.

REFERENCES:1. Winter, K.G., and Brown, C.S., Loads on a Model during Starting and Stopping of an Intermittent Supersonic Wind Tunnel, Royal Aircraft Establishment, 1956.

2. Shimura, T., Mitani, T., Sakuranaka, N., and Izumikawa, M., Load Oscillations Caused by Unstart of Hypersonic Wind Tunnels and Engines, Journal of Propulsion and Power, Vol. 14, No.3, 1998.

3. Maydew, R. C., Compilation and Correlation of Model Starting Loads from Several Supersonic Wind Tunnels, Sandia Rept., SC-4691 (RR), June 1962.

KEYWORDS: aerodynamics, static loads, transient loads, high-speed flows, model injection

AF171-020 TITLE: Instrumentation for carbon-carbon structures in extreme environments

TECHNOLOGY AREA(S): Air Platform

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop and validate, through testing, a methodology to integrate pressure, acoustic, and temperature (from which heat flux may be derived) sensors for carbon-carbon structures to be used as test articles in arc jet facilities.

DESCRIPTION: The Air Force needs a methodology to instrument carbon-carbon structures designed to be tested in arc jet facilities. How to instrument metallic test models is now an ordinary process for standard instruments such as pressure and acoustic transducers and thermocouples. However, there is still a lot to learn on how to instrument carbon-carbon structures without compromising the structural integrity of the test article. The non-isotropic nature of the material also complicates the measurements and data reduction. This topic is mostly concerned with incorporating existing pressure and acoustic transducers, as well as thermocouples (from which heat flux values may be deduced) and/or heat flux gages into carbon-carbon test articles. A key objective is that the incorporation of the transducers does not compromise the performance of the instruments. For example, if the transducer has a high frequency response, it is desired to keep that unaltered. For thermocouples, if measurements need to be made at embedded locations, then the effect of heat conduction through the materials needs to be taken into account when a measurement is being calculated from the readings obtained. Transducers that don’t require active cooling are preferred. It is also desirable that if a transducer fails it can be replaced and installed in the same location. If the instrument needs thermal isolation from the test article, those issues need to be addressed as well. Careful consideration needs to be placed on sealing the transducer housings. The sensors must be installed in structures that

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sustain surface temperatures up to 3000°F during testing.

Both high frequency and mean measurements of pressure and temperature / heat flux are needed to understand the flow field around any test article to be tested in an arc-jet facility. We rely on these measurements to deduce the heat fluxes on the test article and to understand the characteristics of laminar and fully turbulent flows.

In Phase 1, proposers shall choose, taking into account transducers previously demonstrated at arc-jet facilities, at least one type of pressure and acoustic transducer and one type of thermocouple and/or heat flux gage to be integrated to a carbon-carbon structure. The proposer should design a process of integration for all the transducers chosen. Finally, the proposers shall perform bench top experiments where the transducers are installed, checked for leaks, and tested using simple controlled test conditions. Preliminary checks of the structural integrity of the structure should be completed. Also a methodology to replace transducers in the same location should be created.

In Phase 2, proposers shall refine the installation methodology identified in phase I and complete a set of runs in an arc-jet facility. It is recommended that a canonical geometry is chosen for which there is reliable historical data of similar measurements at similar free-stream conditions so that the measurements can be accurately compared. The instruments should be subjected to as many tests as practically possible so that an initial assessment of the robustness of the installation methodology is completed, and the precision, accuracy and frequency response of the transducers used can be checked against historical data. At least one transducer for each type of measurement should be replaced and tested again to assess the effectiveness of the transducer replacement methodology developed in Phase I.

PHASE I: Choose at least 1 type of pressure and acoustic transducers as well as 1 type of thermocouple or heat flux gage to be integrated to a carbon-carbon structure. Create a process for integrating all the transducers chosen into a test coupon. Perform bench top experiments using simple controlled test conditions. Preliminary checks of the structural integrity of the structure should be completed.

PHASE II: Refine the Phase I integration methodology and test an instrumented model in an arc jet facility. Use a canonical geometry to compare the results with historical data of similar measurements at similar free-stream conditions. Test as many times as practical so that an initial assessment of the robustness of the installation methodology is made, and the precision, accuracy, and frequency response of the transducers can be compared with historical data.

PHASE III DUAL USE APPLICATIONS: The instrumentation integration methodology could be patented and offered to the USG, industry, and academia.

REFERENCES:1. David Glass, Ray Dirling, Harold Croop, Tim Fry, Geoffrey Frank, Materials Development for Hypersonic Flight Vehicles, AIAA 2006-8122

2. Timothy Wadhams, Michael Holden, Matthew Maclean, Charles Campbell, Experimental Studies of Space Shuttle Orbiter Boundary Layer Transition at Mach Numbers from 10 to 18, AIAA Paper 2010-1576

3. Tim Roediger, Helmut Knauss, Boris V. Smorodsky, Malte Estorf, Steven P. Schneider, Instability Waves Measured Using Fast-Response Heat-Flux Gauges, Journal of Spacecraft and Rockets, Vol. 46, No. 2, pp. 266-273, 2009

4. Michael A. Kegerise, Shann J. Rufer, Unsteady Heat-Flux Measurements of Second-Mode Instability Waves in a Hypersonic Boundary Layer, AIAA Paper 2016-0357

KEYWORDS: Carbon-Carbon structures instrumentation, temperature sensor, pressure sensor, hypersonic flow, arc jets facility

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AF171-021 TITLE: Ultradense Plasmonic Integrated Devices and Circuits

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop ultradense, low-power plasmonic integration components and devices for future battlefield sensors and systems.

DESCRIPTION: The use of surface plasmons in guiding metallic structures is one of the most promising approaches for overcoming the diffraction limit of light and significantly increasing levels of integration and miniaturization of integrated optical devices and components. The unique properties of plasmonic waveguides (such as very high mode confinement, ultrasharp bends, etc) promises the level of integration optical components, previously unachievable with any other technology. However, significant advancements in both the design and fabrication of both passive and electro-optically active plasmonic structures are required to transition this technology to practical applications. For example, due to very high dimensional tolerances of plasmonic devices electron-beam lithography is typically used for patterning of plasmonic waveguides, which is slow and expensive process, incompatible with large scale production and low costs, required by military and commercial applications. On the other hand, significant advances in nanofabrication techniques made over the last decade may provide the means to solve this problem. For these reasons, advancements in both theoretical understanding of plasmonic integrated circuits and fabrication techniques is required.

Future battlefield systems will exploit highly sophisticated optical communication and signal processing systems with very high component integration density, low power consumption, fast and low-cost data transfer rates. Successful completion of this program will lead to the development of high quality, robust, photonic circuits that will serve as an integrating medium for optical components and networks and that will perform basic, on-chip functions (such as signal conditioning and signal processing).

PHASE I: Demonstrate feasibility of the ultradense plasmonic components and circuits by modeling. Design an active integrated photonic structure and select the materials and fabrication methods. Demonstrate the validity of key processes. Identify the application, develop a documented set of performance parameters and suggest a viable transition to manufacturing strategy.

PHASE II: Build upon Phase I work and fabricate functional passive plasmonic devices. Design and fabricate and demonstrate the functionality of active plasmonic devices. Address the integration of the developed plasmonic circuits into existing or future communication systems. Demonstrate the scalability of the fabrication process to the large-scale low-cost production in Phase III.

PHASE III DUAL USE APPLICATIONS: Applications of the ultradense integrated photonic components in sensors, signal processing and communications. Commercial application: Enable fabrication and design of optical ultradense functional optoelectronic (OE) circuits for optical communications and optical signal processing.

REFERENCES:

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1. T. Nikolajsen and K. Leosson, S. I. Bozhevolnyi, Surface plasmonic polariton based modulators and switches operating at telecom wavelengths, Appl. Phys. Lett., 85, 5833-5835 (2004).

2. S. I. Bozhevolnyi, V. S. Volkov, D. Devaux, J. Laluet & T. W. Ebbesen, Channel plasmonic subwavelength waveguide components including interferometers and ring resonators, Nature, 440, 508-511 (2006).

KEYWORDS: signal processing, optical components, optical subcomponents, photonic integration, optical processors, nanotechnology, plasmonics, meta-materials, nanofabrication.

AF171-022 TITLE: Advanced back-illuminated CMOS image sensors for adaptive optics applications

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

OBJECTIVE: Develop a high-speed, low-noise scientific camera using a back-illuminated silicon CMOS image sensor capable of operating at high quantum efficiency (>80%) without the use of microlenses for use in advanced adaptive optics applications.

DESCRIPTION: Low-noise, high-speed, scientific cameras are the backbone of adaptive optics (AO) applications, and are used in a wide range of applications from wave-front sensing to tilt control. Currently, charge coupled device (CCD) image sensors are the technology of choice for these, and other demanding imaging applications. The technology is well established, and enables high quantum efficiency (QE) to be achieved over the wavelengths of interest. Alternatively, complementary metal-oxide semiconductor (CMOS) image sensors offer potential performance advantages over CCDs. These advantages include lower read noise, the possibility for integrating the imaging system on chip, the provision of digital outputs, and a reduction in overall processing cost by leveraging existing CMOS digital processing technology. However, CMOS image sensors have yet to enter the high-specification scientific imaging market on a large scale, especially for AO applications operating in extremely low-light conditions. Standard front-side illuminated CMOS image sensors suffer from a reduction in QE since there is a light mask over the electronic circuit contained in each pixel, ultimately reducing the sensitivity of the device. In some applications, the QE can be increased through the use of microlenses to direct photons to the light-sensitive areas of each pixel. However, the use of microlenses is not suitable for wavefront sensing and other high performance science applications as photons are not absorbed uniformly across the device. Thus, a back-side illuminated CMOS image sensor with high QE and sensitivity is desirable for high-specification, low-light AO applications. In principle, it should be possible to back-thin existing CMOS image sensors to obtain the same, or better, performance as the CCD.

This solicitation seeks exploration into the design, development, and demonstration of a high-speed, low-noise, scientific camera using a back-side illuminated 128 × 128 (minimum) silicon CMOS image sensor for use in advanced AO applications. The sensor is expected to demonstrate QE above 80% (at 570 nm) without the use of microlenses.

Additional performance objectives for the sensor are (1) full frame rates above 5 kHz, (2) low read-noise below 3 e- at a 5 kHz frame rate, (3) true on-chip binning, (4) efficient windowing geometry for high frame rates, (5) oversampling through non-destructive reads to reduce read-noise at lower frame rates, (6) high linearity over the dynamic range of the imager for each pixel, and (7) the use of the camera-link communication protocol.

PHASE I: Perform preliminary analysis and conduct trade studies to identify a suitable silicon CMOS image sensor. Work with foundry partners to implement back-thinning, anti-reflection coating, and packaging processes to solve the fill-factor and QE issues associated with the front-side illuminated sensor.

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PHASE II: Integrate the packaged back-illuminated CMOS sensor into a controller which uses a standard camera-link interface protocol to meet the stated performance requirements. Test and validate device performance. Further work is desired to complete specialized chip fabrication runs to incorporate skipping throw-away-guard-column (TAGC) mode to double the frame rate (or half the latency), and to optimize the read-out electronics for more specialized wavefront sensor (WFS) applications.

PHASE III DUAL USE APPLICATIONS: Develop technology applicable to high-specification science-imaging applications.

REFERENCES:1. Paul Jerram; David Burt; Neil Guyatt; Vincent Hibon; Joel Vaillant, et al. "Back-thinned CMOS sensor optimization", Proc. SPIE 7598, Optical Components and Materials VII, 759813 (February 25, 2010); doi:10.1117/12.852389.

2. James R. Janesick ; Tom Elliott; Stewart Collins; Morley M. Blouke and Jack Freeman, "Scientific Charge-Coupled Devices", Opt. Eng. 26(8), 268692 (Aug 01, 1987).

3. Daniel Durni; David Arutinov; Martin Lesser, et al. “High performance silicon imaging: fundamentals and applications CMOS and CCD sensors”, Woodhead Publishing Ltd. Edition: 1st (May 28, 2014).

KEYWORDS: Image Sensor, Science Camera, CCD, CMOS, Back-Illuminated, Back-Thinned, Adaptive Optics

AF171-023 TITLE: Adaptive Optics Prototype for a Meter-class Telescope used for Space Surveillance

TECHNOLOGY AREA(S): Space Platforms

OBJECTIVE: Build and demonstrate an adaptive optics prototype which can be deployed at 1 m class telescopes for the Space Surveillance Network (SSN) to accomplish characterization of Low Earth Orbit (LEO) objects and area inspection around high value assets at Geosynchronous Earth Orbit (GEO).

DESCRIPTION: The goal of this project is to design, build and test an adaptive optics (AO) system which can be deployed to 1 m class telescopes at an AFRL or at a Ground-based Electro-Optical Deep Space Surveillance (GEODSS) site. An affordable AO system would enhance the value of future meter-class telescopes developed for the Space Surveillance Network (SSN). The AO system shall be flexible enough to be integrated with telescopes ranging between 0.5 m - 1.5 m. The system field of view (FOV) should allow for imaging Low Earth Orbit (LEO) objects and spatially separating closely-spaced Geosynchronous Earth Orbit (GEO) objects.

An effective AO system shall presumably include a tracker, a low-order mode corrector - steering mirror (SM), a high-order mode corrector - deformable mirror (DM) or micro-electro-mechanical system (MEMS), an established wavefront sensor, an auxiliary path to split the visible light to a second novel WFS, an imaging camera, reconstruction algorithm, software, and an interface mechanism that allows closed-loop communication between the corrector elements, the WFS, and the reconstruction algorithm. The AO system should be able to correct a range of seeing between 0.7 to 2 arcseconds at 500 nm. The servo loop shall be able to run at kilo-hertz speeds. For the imaging camera, the number of pixels selected and the pixel pitch shall be able to sample D/r0 = 20. The system shall record reconstructed wavefronts from the visible WFS, and I-band or J-band PSFs from the imaging camera. A mechanism is needed to either allow all the light to the baseline WFS or different percentages (25%, 50%, 75%, 100%) of light to the baseline WFS while sending the remaining light to the auxiliary WFS. The design, construction, and integration of the second WFS is independent of this SBIR. Successful bidders will to the greatest extent possible show:

1. Ability to design and build an AO system adhering as much as possible to the previous description and based as

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much as possible on COTS parts. Provide a conceptual optical design with FOV specifications. Include a conceptual electrical design.2. Ability to design, code, and test a reconstruction algorithm that is linear, has a high dynamic range and allows user modification. 3. Ability to integrate rapidly with a telescope for on-sky testing (target < 4 weeks). The baseline is a 1 m telescope with f/100 and a connected coude room operated by AFRL at the Starfire Optical Range. 4. Ability to build a compact AO system which can be transported to potential GEODSS sites.5. Ability to switch rapidly (minutes) between the base-line WFS and the auxiliary novel WFS without effecting alignment. 6. Ability to deliver specifications and performance metrics for the scoring, WFS, and imaging cameras.7. Ability to accurately predict and model telescope hardware and AO system performance as well as photometric and radiometric performance for objects of mv = 7 - 14 magnitude. Derive a metric for observing closely-spaced objects.8. Show understanding of the cost of, hardware, people-hours required to assemble and interface the AO system, and software development.9. Ability to provide follow-on use of the AO system and the software by the Air Force under a cooperative agreement to be arranged in the future.

PHASE I: Carry out simulations to test the performance of the AO system in conjunction with the listed metrics. Design an AO system that can be integrated with a 1 m class telescope using metrics given above, especially being able to correct seeing between 0.7 - 2 arcseconds at 500 nm, operate at kilo-hertz speeds, and sample D/r0 = 20. The system should be built for a coude room but be compact enough to be transportable. Provide a cost-estimate for the hardware, software, and people-hours required to design, build, and integrate the system.

PHASE II: Work in consultation with the government to build and install the AO system on a 1 m telescope. Carry out on-sky observation with the AO testbed using different magnitude (mv = 7 - 14) sources as well as different separations (3 lambda/D - 4 lambda/D). From the observations record reconstructed wavefronts from the WFS and corrected PSFs from the imaging camera. Provide a report on system performance based on metrics and goals outlined in the description.

PHASE III DUAL USE APPLICATIONS: Integrate and demonstrate one or more AO systems. Work with the government to operate the prototype to conduct an SSA mission. Analyze the performance of the AO system using the metrics in the description. Prepare a final report on the AO prototype.

REFERENCES:1. J. W. Hardy. Adaptive Optics for Astronomical Telescopes. Oxford University Press, July 1998.

2. Fugate et. al. Experimental Demonstration of Real Time Atmospheric Compensation with Adaptive Optics Employing Laser Guide Stars. BAAS, Vol. 23, p. 88, March 1991.

3. O. Guyon. Limits of Adaptive Optics for High-Contrast Imaging. ApJ, 629:592–614, August 2005.

KEYWORDS: Adaptive Optics, AO, wavefront sensors, WFS, Shack Hartmann wavefront sensor, SHWFS, Ground-based Electro-optical Deep Space Surveillance, GEODSS, Space Surveillance Network, SSN, Space Situational Awareness, SSA

AF171-024 TITLE: Daylight Glare Reduction Using a Light-field Camera

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

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OBJECTIVE: Improve glare reduction/rejection in daylight satellite tracking operations caused by close proximity to the Sun, reducing the exclusion angle around the Sun.

DESCRIPTION: The USAF requires the ability to track space objects in daylight. At present the Air Force daylight tracking telescopes are excluded from the area within about 15 degrees of the Sun due to glare that baffles are not able to block. Current methods of reducing glare involve modifying the telescope and the optics, e.g. baffles and optics coatings. The Directed Energy Directorate is interested in identifying and investigating technologies that could be applied to reduce or reject solar glare inexpensively. We are looking for innovative ways to reduce this exclusion zone to less than 15 degrees. Two concepts that have caught our eye are coded apertures and modulo cameras. Coded apertures have been shown to be effective in removing glare in terrestrial photography and we believe that it may have use in reducing the solar glare in daylight observations. The modulo camera uses a technology that removes the effects of glare/over exposure at the chip level, while leaving the unsaturated areas of the chip as they are. The over exposed areas are then computationally re-inserted with the result being an image showing no overexposed pixels. Both of these technologies show promise that these and/or other new techniques / technologies could be applied to meet the Air Force need to minimize the exclusion zone around the Sun.

Modeling and simulation are highly desired to guide in the development of this technology. Software derived to improve image processing is also of interest. Development of a prototype device in Phase II that can be used to demonstrate the glare reduction is the principal goal of this SBIR.

We believe any technology that meets the Air Force's needs could also be used in military or non-military applications for tracking airborne missiles, projectiles, aircraft, and even birds in close proximity to the Sun using optical systems.

There is no requirement for the use of government materials, equipment, data, or facilities in the execution of this SBIR. The developed technology concept shall be demonstrated on commercial-off-the-shelf equipment to show its effectiveness in a generic telescope system.

The technologies cited are just examples of potential technologies for this program and are not meant to limit exploration of other innovative technological solutions.

PHASE I: Identify technologies for reducing solar glare while tracking orbiting objects that visually pass close to the Sun. Perform modeling and simulation to determine technologies to reduce glare effects. Develop an initial concept design of the most promising technological solution. Produce a detailed analysis of predicted performance for this concept to reduce the exclusion angle by 25% with comparison to current glare reduction methods.

PHASE II: Develop, test, and demonstrate a prototype glare reducing sensor system, including any software and processing. This sensor system must be readily adaptable to work on standard, commercial-off-the-shelf telescopes (Meade, Celestron, etc.). Assess the utility and skill level required for implementation to carry out observations in the field under both ideal and non-ideal conditions (e.g., extreme temperatures or high humidity).

PHASE III DUAL USE APPLICATIONS: Manufacture and market sensors for customers who will be tracking objects that pass visually close to the Sun. Since the envisioned concept would be optics-agnostic it should open a wider field of customers who could benefit from this technology using standard lens assemblies.

REFERENCES:1. http://www.cs.cmu.edu/~ILIM/projects/IM/aagrawal/sig08/index.html.

2.http://web.media.mit.edu/~hangzhao/modulo.html.

KEYWORDS: glare reduction, daylight observation, satellite tracking, solar exclusion angle

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AF171-025 TITLE: Realtime Multiframe Blind Deconvolution (MFBD) for Imaging through Turbulence

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a standalone processing unit that applies a multiframe blind deconvolution (MFBD) algorithm to an input stream of live, turbulence-degraded satellite imagery. Corrected image estimates should be displayed to the user in real-time.

DESCRIPTION: Applications such as ground-based space imaging, remote sensing, and target identification must contend with real-time atmospheric fluctuations that distort optical imagery. Adaptive optics (AO) can be used to mitigate atmospheric and local optical distortions; however, even with AO, residual distortions generally prevent an optical system from achieving diffraction-limited resolution for a variety of reasons. Moreover, some applications may not support the beacon requirements or additional size, weight, power, and cost (SWaP-C) of adding AO to an optical system.

The aim of this topic is to develop the capability to apply MFBD image reconstruction to both AO compensated and uncompensated camera imagery in near-real-time. Generally MFBD is used as a post-processing technique to remove residual imaging distortions over a set of images. It is assumed that within an image set, the object of interest does not change significantly and that each frame contains a different point spread function (PSF) due to the turbulent media. Depending on the particular MFBD algorithm, varying further assumptions can be made. For the Phase I and II efforts, proposals should focus on algorithms tailored to turbulence degraded imagery of resolved space objects. Reference [1] presents an overview of MFBD techniques and some variations. More recent research on alternate MFBD techniques can be found in the literature. Proposals should motivate specific the algorithm(s) chosen.

Currently, MFBD requires significant computational time and/or super computer resources to process image sets. This effort aims to leverage emerging massively parallel computing hardware to provide the real-time MFBD capability from a standalone computing system. Bidders are not restricted to any particular hardware scheme, leaving the door open for a range (or mix) of computing technologies. Image frames up to 512x512 pixels may be provided at up to 200Hz, and reconstructed images should be displayed at a minimum of 2Hz to the user. The system should adjust accordingly as frame rates or frame sizes are changed without significant effort to the user. A number of frame queuing strategies could be envisioned, and bidders will be expected to motivate a particular strategy in their Phase I efforts. It is expected that some level of interfacing will be needed to provide the system with the most recent camera dark captures corresponding to specific camera settings.

Proposed designs will be evaluated based upon the following criteria (in this order): 1) Achievable frame rates 2) Reconstructed image quality 3) Hardware and software scalability 4) System cost 5) System size (Ideally a single computing tower)

Clearly, expansion to video frame rates (20 – 60Hz) opens the door to a range of applications. Further, this technology could enable larger apertures for applications that were previously atmospheric seeing limited and lack

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feasibility for AO.

A number of additional references are provided: Reference [3] highlights a real-time image enhancement processor, which provides incremental image enhancement without the complexity of MFBD. This can be considered the current state-of-the-art capability. Reference [4] presents an algorithm that merges multiple sensor feeds from different spectral bands. While not required for this effort, this is an algorithmic variation that may be interesting to investigate if the computational resources permit. Other variations may be proposed, including exploiting additional system state information (e.g. wavefront sensor gradients, high-bandwidth scoring camera measurements, r0); however, proposals utilizing additional data feeds should anticipate additional interfacing effort required for the Phase II deliverable.

PHASE I: Identify the specific MFBD algorithm(s) to implement. Develop a scalable software and hardware architecture implementing the selected MFBD algorithm(s). Demonstrate image correction capability, given multiple short-exposure image collection sequences of varying classes of space objects. Demonstrate understanding of how the proposed system architecture would scale to support real-time operation.

PHASE II: Build a real-time system implementing the selected MFBD algorithm(s) driven by live sensor feeds. Collaborate with government personnel to develop any necessary camera interfacing. Develop a user-friendly graphical interface to control relevant operational parameters and to view the real-time corrected imagery. Demonstrate the robustness of the control interface and real-time MFBD-enhanced imagery. Identify future upgradeability and anticipated performance gains possible (or potential limits).

PHASE III DUAL USE APPLICATIONS: Develop and execute a plan to market and manufacture the product system. Identify and execute algorithmic, architecture, or interface modifications required to support other applications such as remote sensing, target ID, optical tracking, and medical imaging. Maintain relevance as hardware advances

REFERENCES:1. Charles L. Matson, Kathy Borelli, Stuart Jefferies, Charles C. Beckner, Jr., E. Keith Hege, and Michael Lloyd-Hart, "Fast and optimal multiframe blind deconvolution algorithm for high-resolution ground-based imaging of space objects," Appl. Opt. 48, A75-A92 (2009).

2. Michael Werth, Brandoch Calef, Daniel Thompson, Kathy Borelli, and Lisa Thompson, “Recent improvements in advanced automated post-processing at the AMOS observatories,” Proceedings of IEEE Aerospace, March 2015.

3. David R. Gerwe and Paul Menicucci, “A real time superresolution image enhancement processor,” Proceedings of AMOS, Sept. 2009.

4. Daniel Thompson, Michael Werth, Brandoch Calef, David Witte, and Stacie Williams, “Simultaneous processing of visible and long-wave infrared satellite imagery,” Proceedings of IEEE Aerospace, March 2015.

KEYWORDS: multiframe blind deconvolution, image reconstruction, image processing, remote sensing, adaptive optics

AF171-026 TITLE: 24/7 Monitoring of Active Satellites using Passive Radio-Frequency (RF) Sensors

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

OBJECTIVE: Deliver a passive radio-frequency sensor for maintaining track custody and unique identification of actively RF-emitting satellites from low-earth orbit (LEO) to geosynchronous orbit (GEO) 24 hours per day through

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cloud cover with reasonable cost.

DESCRIPTION: The Air Force ground-based electro-optic (EO) sensor sites, such as the AFRL Dynamic Optical Telescope System at Maui, conduct monitoring of resident space objects (RSOs) both at LEO and GEO, but the mission of such facilities is limited by cloud-cover and daylight. Radio-frequency (RF) sensors can monitor RSOs 24 hours per day and through clouds, but radar techniques become expensive for tracking RSOs, especially GEOs. Passive-RF techniques could augment the ground-based EO networks with cost per site potentially comparable to a 1-meter telescope facility, and their operations are almost unlimited by weather and daylight. To be most useful, a passive-RF sensor system or family-of-systems would track and uniquely identify both RF-emitting LEOs and GEOs, and the passive-RF sensor system would report detection of a moving satellite in about a minute. For GEO, the passive-RF sensor system would maintain custody of several satellites per hour, likely in a patrol mode in which satellites are revisited in prescribed time intervals on a diurnally-persistent basis, reporting on detected maneuvers of satellites which are inconsistent with their normal station-keeping routines. These reports could be used to alert another satellite-monitoring facility to follow the maneuvering satellite. In addition, for GEOs the passive-RF sensor would uniquely-identify and spatially-distinguish satellites appearing close together along the line-of-sight. For this project, the successful bidder will to the greatest extent possible show:

1. Ability to design, build, and deliver a passive-RF sensor system(s) that can detect and track either RF-emitting LEO or GEO satellites or both with this performance: a. Suffers minimal loss of performance through a diurnal cycle and when cloudy along the line-of-sight.b. Produces track accuracy < 2 arcseconds RMS.c. Distinguishes the unique RF signature of a satellite and identifies the satellite with the closest-matching SATCAT number. Here, the word distinguish is not equivalent to deciphering the satellites communication stream.d. Derives an orbital fit, such as a two-line element set and state vector, from observations.e. Tracks when the solar separation angle to the satellite is greater than or equal to 10 degrees with < 25% reduction in signal-to-noise ratio.f. For GEOs: tracks greater than or equal to 10 satellites per hour with a revisit period < 30 minutes. Also, show the ability to execute changes to the list of satellites being monitored in less than 8 hours.g. For LEOs: derives a track by the time the elevation angle to the horizon from the satellite exceeds 10 degrees.2. Ability to put a sensor at a customer designated site, assuming site already has power and internet. Potential sites include the Maui Space Surveillance Site, Kirtland Air Force Base, Wright-Patterson Air Force Base, the GEODSS Test Site in Colorado and other government-owned facilities in the United States.3. Ability to produce a sensor with supporting facility and software with low-cost (objective < 1Million dollars per site).4. Ability to distribute an orbital fit to a government customer rapidly: objective for GEOs < 5 minutes and for LEOS < 1 minute.5. Ability to accurately show the design is likely to succeed. Also, show traceability from a prototype sensor to an objective sensor that the Air Force would put into the field.6. Ability to provide follow-on use by the Air Force under a cooperative agreement to be arranged in the future.

PHASE I: Design a passive-RF sensor that uniquely identifies, tracks, and reports position & velocity of an RF-emitting LEO or GEO or both. Show the design(s) is likely to succeed. Develop an experiment plan with the customer to demonstrate the passive RF sensor can cue an EO sensor. For GEO, suggest a threshold for detecting a "change". Deliver an estimate of the life cycle cost for an objective system.

PHASE II: After consulting the customer, build a prototype sensor(s) and demonstrate that it can cue a customer EO sensor to rapidly locate and track a satellite through a mixture of full-day and full-dark conditions for the RSO and the EO-site. For LEO, demonstrate track hand off during the same above-the-horizon pass. For GEOs, select 15 and show the prototype maintains track custody 24-hours per day for > 15 days. Show track accuracy of < 2 arcseconds when the line-of-sight is cloudy at the RF site.

PHASE III DUAL USE APPLICATIONS: In consultation with the customer, build and demonstrate a passive-RF sensor unit ready to deliver to the field and provide an estimate of the life cycle cost. Deliver, install, and verify operation of at least one sensor unit and supporting components to an Air Force satellite-monitoring facility.

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REFERENCES:1. Development of a passive satellite tracking sensor, Gilgallon, P.F. et al, 1999, AIAA-99-4530 (http://arc.aiaa.org/doi/10.2514/6.1999-4530).

2. Estimation, tracking and geolocation of maritime burst signals from a single receiver, Nelson, D.J. et al., 2015, Proc. SPIE 9476.

3. Cross-spectral TDOA and FDOA estimation, Nelson, D.J. et al., 2015, Proc. SPIE 9090.

4. Space-based detection of spoofing AIS signals using Doppler frequency, S. Guo, 2014, Proc. SPIE 9121.

KEYWORDS: space, situational, awareness, SSA, radio-frequency, RF, passive, satellite, GEO, LEO, RSO, low-cost, cloud, custody, diurnal

AF171-027 TITLE: Cyber warfare laboratory design

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Development and demonstration of cyber warfare laboratory.

DESCRIPTION: The US Air Force has interest in quantifying the effects of cyber warfare on its systems. In order to ensure that weapons systems are adequately protected against cyber-attacks, the AF desires to design/develop a plug-and-play cyber sand box laboratory with safeguards to allow testing of computer/electronic devices against those attacks. This laboratory should be able to interface and test different AF hardware/systems to evaluate effectiveness of cyber security systems against variety of attacks. The laboratory and the equipment tested should be able to be reused after each attack, and not be permanently contaminated. Consider philosophies akin to Chem/Bio clean room techniques to prevent contamination inside and outside of cyber lab environment. Infrastructure considerations, such as but not limited to scenario generation and management, performance assessment, after-action review and feedback, should address instruction and training applications.

Need capability to test a line-replaceable unit or subsystem of ICBMs or air delivered weapon systems in a benchtop test bed. The purpose of this study is to identify and isolate the Air Force data protocols and how to set up plug-and-play interfaces with can be used for threat injection and system response evaluation.

Attack types include: denial of service attacks, disabling attacks, to include, malware, viruses, worms, Trojan horses, etc. that can be done via TCPIP or other AF standard data protocols, that will affect weapon system reliability and mission effectiveness.

The cyber lab design could be for either a fixed or portable lab. This is a design parameter that needs to be studied in this SBIR study. This design parameter will have to weigh accessibility/ease of use with security/isolation.

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The purpose of this study is to determine the necessary design parameters to successfully build a cyber lab.

Only contractors able to obtain a Secret level security clearance should submit proposals against this topic.

PHASE I: Design a cyber warfare lab for basic cyber environment architecture, cyber-attack, AF test asset incorporation (plug-and-play), basic protocols for aseptic, sterilization & disposal procedures, high reuse of cyber infrastructure to minimize costs, data capture system, measures of perf for system sterility & effectiveness of attack. Design should also address instruction & training applications.

PHASE II: Develop a detailed design of the cyber laboratory expanding upon the items addressed in phase-I at an actionable-level. Only contractors able to obtain a Secret level security clearance should apply.

PHASE III DUAL USE APPLICATIONS: Manufacture & test a portable/ small-scale version of the cyber warfare lab defined by the USAF sponsor to verify the manufacturability & performance the lab. Private companies may have interest in testing cyber security systems. Government has interest in evaluating effectiveness of systems.

REFERENCES:1. U.S. Department of Defense, Cybersecurity, Instruction 8500.01, Washington, D.C.: DoD Chief Information Officer, 14 March 2014.http://dtic.mil/whs/directives/corres/pdf/850001_2014.pdf.

2. Advanced Cyber Attack Modeling, Analysis, and Visualization, George Mason University for Air Force Research Laboratory, Rome, New York, March 2010http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA516716.

3. Drew, John G., George E. Hart, Kristin F. Lynch, Don Snyder, Ensuring U.S. Air Force Operations During Cyber Attacks Against Combat Support Systems, Santa Monica, CA: RAND Corporation, 2015http://www.rand.org/pubs/research_reports/RR620.html.

4. Libicki, Martin C., Cyberdeterrence and Cyberwar, Santa Monica, Calif.: RAND Corporation, MG-877-AF, 2009. As of December 29, 2013:http://www.rand.org/pubs/monographs/MG877.html.

5. PorcheIII, Isaac R., Jerry M. Sollinger, Shawn McKay, A Cyberworm that Knows no Boundaries, Santa Monica, CA: RAND Corporation, 2011http://www.rand.org/pubs/occasional_papers/OP342.html.

6. Schmorrow, D., Cohn, J., & Nicholson D. (Eds). (2009). The PSI Handbook of Virtual Environments for Training and Education: Developments for the Military and Beyond. Volume 1: Learning Requirements, and Metrics. Westport, CT: Praeger Security International.

KEYWORDS: Cyber Security

AF171-028 TITLE: Cyber Attack model using game theory

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of

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sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Development and demonstration of a Cyber Attack model using game theory.

DESCRIPTION: As cyber-attacks continue to grow in number, scope, and severity, the cyber security problem has become increasingly important and challenging to US Air Force strategic weapons community. The US Air Force has interest in quantifying the effects of cyber warfare on its systems. In order to ensure that weapons systems are adequately protected against cyber-attacks, the AF desires to design/develop a modeling and simulation scheme that can best identify paths within our weapon systems that are most vulnerable.

Researchers have recently started exploring the applicability of game theory to address the cyber security problem. The weakness of traditional network security solutions is that they lack a quantitative decision framework. As game theory deals with problems where multiple players with contradictory objectives compete with each other, it can provide us with a mathematical framework for modeling and analyzing cyber security problems.

The US Air Force is interested in working with industry in developing a game theory based modeling and simulation that could be used for all strategic systems and for cyber security training applications. These strategic systems include ICBMs, Bombers, Cruise Missile, Gravity Bombs, and Nuclear Command, Control and Communications.

The US Air Force will provide data as needed for the selected system for the contractor's proof of concept (e.g., ICBMs, Bombers, Cruise Missile, Gravity Bombs, and Nuclear Command, Control and Communications). The US Air Force is not asking for a separate model for each system. The Air Force is asking for a proof of concept that can be scalable up to a whole mission system. The US Air Force will not provide material/equipment.

Only contractors able to obtain a Secret level security clearance should submit proposals against this topic.

PHASE I: Develop a preliminary design of a cyber-attack model to quantify the effects of cyber warfare on U.S. Air Force systems. Identify design components required to enable training applications. Establish feasibility and technical merit of proposed solution through modeling, and design analysis. Assess any cost, performance, or security issues and recommend risk reduction activities to address them.

PHASE II: Develop a detailed design of the cyber-attack model expanding upon the design addressed in phase-I at an actionable-level.

PHASE III DUAL USE APPLICATIONS: Develop and test the cyber-attack model defined by the USAF sponsor cyber-attack model to quantify the effects of cyber warfare on USAF systems and enable its use for USAF cyber training. Private companies have interest in modeling cyber-attacks to quantify effectiveness of cyber security systems.

REFERENCES:1. U.S. Department of Defense, Cybersecurity, Instruction 8500.01, Washington, D.C.: DoD Chief Information Officer, 14 March 2014. http://dtic.mil/whs/directives/corres/pdf/850001_2014.pdf.

2. U.S. Air Force, Cyberspace Operations, Washington, D.C.: Department of the Air Force, Air Force Policy Directive 10-17, July 31, 2012.

3. Drew, John G., George E. Hart, Kristin F. Lynch, Don Snyder, Ensuring U.S. Air Force Operations During Cyber Attacks Against Combat Support Systems, Santa Monica, CA: RAND Corporation, 2015

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http://www.rand.org/pubs/research_reports/RR620.html.

4. Libicki, Martin C., Cyberdeterrence and Cyberwar, Santa Monica, Calif.: RAND Corporation, MG-877-AF, 2009. As of December 29, 2013: http://www.rand.org/pubs/monographs/MG877.html.

5. PorcheIII, Isaac R., Jerry M. Sollinger, Shawn McKay, A Cyberworm that Knows no Boundaries, Santa Monica, CA: RAND Corporation, 2011, http://www.rand.org/pubs/occasional_papers/OP342.html

KEYWORDS: Cyber attack, cyber warfare training applications

AF171-029 TITLE: Training for Cyber Operations

TECHNOLOGY AREA(S): Human Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop interactive and immersive training Simulator for Cyber Weapon Systems.

DESCRIPTION: This topic focuses on the development of an interactive and immersive training simulator capability intended to ultimately reduce costs associated with the development of ranges and testbeds for cyber training. Currently, no distributed multi-unit training is available without extensive and costly travel. A capability is required to provide live, virtual, constructive, and distributed multi-unit training. This is needed to minimize costs, avoid operational disruption due to travel for remote training, and to optimize the effectiveness of both individual and inter-unit training. The training environment should reflect a DoD network from the operator perspective, should host all of the tools the operator uses to defend and operate the network, and support the tactical command and control constructs used by the units. The capability should include sensors and storage to capture the live training. Both during training and in after-training reviews, a capability should be available to stop the event and critique the trainees using the actual network traffic. Additionally, the capability should be able to start, stop, rewind, fast forward and jump to any part of the training. Airmen performance in the operational world should have the capabilities to take any dynamic cyber training ranges and leverage the following: scenario authoring, learning management systems, scenario execution engine and performance assessment in a live, virtual, constructive, distributed, and multi-unit training exercise. The goal of this effort will be to create an interactive and immersive training capability to allow variations of live, virtual, constructive, distributed, and multi-unit training needed to train cyber units/crews to the most current state-of-the-art capabilities and training, tactics and procedures available. Furthermore, the simulator should be able to integrate with any systems, cyber ranges, testbed, cyber weapons system or DoD network currently being used by cyber operators.

PHASE I: Identify and define the current state of cyber training capability for the Air Force. Assess our training capabilities and outline a cyber training simulator that can leverage the current architecture and provide training with live, virtual, constructive, distributed, multi-unit exercises. This simulator will have the capability to be used for/with any of the Cyber Weapon Systems.

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PHASE II: Develop, demonstrate and validate the cyber training simulator identified in Phase I. Establish performance parameter through experiments and prototype fabrication. Construct and demonstrate the operation of a prototype training simulator on a cyber ranger in a distributed training exercise with Cyber SMEs. Conduct user and training impact assessments. Complete training simulator design and fabrication. Identify cyber customers and conduct initial evaluations.

PHASE III DUAL USE APPLICATIONS: Implement the cyber simulator capability to each of the identified Air Force Cyber Weapons Systems. Further, refine each part of the simulator in relation to the scenario authoring tool, learning management system, scenario execution engine, and performance assessment.

REFERENCES:1. USAF Core Functions Support Plan: Cyberspace Superiority, 2016.

2. USAF Strategic Master Plan, May 2015.

KEYWORDS: Cyber, cyber weapon system, cyberspace superiority, immersive training, interactive training, live, virtual, constructive, distributed, multi-unit training

AF171-030 TITLE: Battlefield Airmen Augmented Reality System (BAARS)

TECHNOLOGY AREA(S): Human Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a low-latency multispectral digital helmet-mountable near-to-eye augmented reality system for use by Battlefield Airmen. System must be capable of use to aid vision in night, day, and all-weather operations.

DESCRIPTION: The Battlefield Airmen Augmented Reality System (BAARS) sought is multispectral device primarily for night ground operations or in helicopters with open doors. Architectures of interest include: mounting (on helmet, on head, or hand held); sensors (in-line with, or above, eyes); displays (bi-, bin-, mon-, dig- ocular), and bands (multiple reflective and emissive). Most cameras operate by sensing reflected illumination in the 400-700 nm visible (VIS) band. Current analog night vision goggles (NVG) operate by sensing ambient illumination reflected off of scenes in the 625-930 nm near infra-red (NIR) band, which encompasses part of the visible and near infra-red (VNIR) electromagnetic spectrum. However, additional night/day sky illumination energy is available the 0.9-3.5 um short-wave infra-red (SWIR) spectral band. And emissive energy is available in the 3-6 um mid-wave infra-red (MWIR), and 7-15 um long-wave infra-red (LWIR) spectral bands. The SWIR and MWIR band have a unique ability to see through atmospheric obscurants (e.g. fog, haze), improved detection of VNIR camouflage, and detection of out-of-VNIR-band lasers. Terrestrial thermal sources (from e.g. people, engines, cars, animals) emit energy in the MWIR and LWIR bands. However, these longer wavelengths are usable only in the absence of transparencies (lenses in dust goggles, canopies/windows in aircraft) made of materials like BPA-based polycarbonates with transmission cut-off beyond SWIR. The BAARS device shall be battery powered and be capable of displaying symbology/imagery from an external source. The size, mass, mass distribution, and power consumption should be minimized sufficiently to achieve user acceptance. The device should be comfortable for

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wearing under combat conditions for hours. Power and connectivity trade-off considerations include (a) helmet- versus body- mounted batteries and (b) wired versus wireless options for the transmission of both signal and power. Performance metric threshold (objective) sought include: sensor bands VNIR+LWIR (VNIR+SWIR+LWIR or MWIR); image resolution 640x512 px (8 Mpx); field-of-view 40x30 deg. (60x40 deg.); frame rate 60 Hz (200 Hz); latency from objective-to-eye < 20 ms (< 5 ms); head-born mass 1 kg (0.5 kg); head-born moment arm 0.1 kg-m (0.05 kg-m); power 6 W (2 W); volume 1000 cc (500 cc); and head-mounted battery time 1 hr (4 hr).

PHASE I: Design a BAARS with size, weight, and power (SWaP) consistent with head-worn implementation. Estimate all performance metrics via laboratory experiments and analyses. Develop a system architecture for BAARS integration into the dismounted BAO Kit. Develop a System Implementation Plan for evaluating BAARS operating performance in combat environments, including producibility and supportability.

PHASE II: Fabricate a prototype BAARS. Develop a test plan. Evaluate the prototype in a laboratory environment. Demonstrate BAARS mechanical and electrical interfaces for integration into the BAO Kit. Provide special test equipment, support operator testing, and refine prototype performance based on feedback. Deliver prototype BAARS optimized for SWaP performance, reliability, and ruggedization consistent with dismounted warfighter operations. Create a roadmap to mature the technology.

PHASE III DUAL USE APPLICATIONS: Develop BAARS pre-production product and integrate with the BAO Kit. Provide a pre-production BAARS bill of materials. By the end of Phase III, the BAARS should be capable of all-weather operation worldwide. Develop commercial applications.

REFERENCES:1. Fact Sheets: (a) Combat Controllers (18 Aug 2010); (b) Guardian Angel (18 Mar 2013). Available athttp://www.af.mil/AboutUs/FactSheets/Display/tabid/224/Article/104592/combat-controllers.aspx.

2. Jeff Paul, Exploit new spectral band (SWIR) & multi-spectral fusion: MANTIS Program Update, Multispectral Adaptive Networked Tactical Imaging System (MANTIS), WBR Soldier Technology US 2008 Conference (Worldwide Business Res. Ltd.,) Arlington, VA, 15 Jan 2008.

3. Goodrich, http://www.sensorsinc.com/whyswir.html for SWIR sensor data.

4. Peter Burt, On Combining Color and Contrast-selective Methods for Fusion, IDGA Image Fusion Conference, Institute for Defense and Government Advancement, 2004.

5. Raytheon Vision Systems, http://www.raytheon.com/; Intevac Photonics Inc., http://www.intevac.com/.

KEYWORDS: Battlefield Airmen Augmented Reality System, BAARS, digital night vision, day vision, multispectral digital imaging, adaptive fusion, visible, short-/mid-/long- wave infra-red

AF171-031 TITLE: Wearable, Broadband, EM Field Exposure Detection System with Data Sharing Capability

TECHNOLOGY AREA(S): Human Systems

OBJECTIVE: Develop a real-time, wearable battlefield radio frequency field detection system to monitor human exposure to harmful EM fields, notify the wearer, broadcast exposure information for command and control, and improve battlespace situational awareness.

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DESCRIPTION: With ongoing development of radio-frequency (RF) directed energy weapons, it can be expected that warfighters will encounter such weapons on the battlefield. In some circumstances, exposure to DEW is not detectable and injury may occur before individuals have an opportunity to react. Experience has shown that the best way to avoid injury from DEWs is to notify individuals when they are exposed so they can leave the area. Therefore, it is necessary to equip warfighters with safety equipment that can give an indication when exposure occurs. Additionally, it is important to share this information with C2 and other warfighters on the same battlefield to increase leadership’s command ability and increase the warfighter’s situational awareness.

Off-the-shelf RF safety equipment exists. Technicians in the telecommunication industry, for example, routinely employ hand-held devices that measure electric field strength or power density of ambient RF fields. Such equipment, however, is not suitable for military personnel because it is bulky and fragile. Furthermore, existing safety devices provide indication of exposure, but don’t give broadband indication of risk to the operator in real time. In addition, current safety devices have no capability in aiding situational awareness for C2 and the warfighter.

To mitigate these shortfalls, a new RF detection system must be developed. The system will need to be hands free, wearable, and a maximum of 5 lbs. It will need to determine the frequency, intensity, and duration to RF fields between 10kHz and 300GHz. It must determine the location of the wearer during an exposure incident. It will need to compare the exposing RF field strength with the frequency dependent maximum permissible exposure (MPE) determined by IEEE C-95.1 and AFI 6055.11. It will need the capability to give multi-step audio and visual warnings to the warfighter depending on the intensity with respect to the MPE. The system will need to share data with other units within 100 meters to display all troop exposures on the battlefield on a common map to aid in C2 and warfighter situational awareness. Finally, each unit must have the capability to relay data between other devices to enable communication beyond the 100 meter range.

PHASE I: Design a system to meet the defined specifications. Demonstrate through laboratory testing that the system design will meet specifications and identify areas where the specifications cannot be met with new technology. Identify promising technology development that will allow improvement beyond the scope of the Phase I SBIR effort.

PHASE II: Develop a prototype system that implements the system as designed in Phase I. Collaborate with government personnel to test the prototype in a simulated operational environment.

PHASE III DUAL USE APPLICATIONS: Develop a commercial system that can be used by industries to improve RF detection and safety. Identify potential customers beyond the sponsor of this project and create a commercialization plan for the system.

REFERENCES:1. DoD Instruction 6055.11, Protection of DoD Personnel from Exposure to Radiofrequency Radiation. 2009.

2. IEEE Standard for Safety Levels with Respect to Human Exposure to Radio Frequency Electromagnetic Fields, 3kHz to 300 GHz. Santa Ana, Calif.: Global Engineering Documents, 2006.

KEYWORDS: Wearable, Detection, Safety, Command & Control, Warfighter, Battlefield

AF171-032 TITLE: Wearable Device to Characterize Chemical Hazards for Total Exposure Health

TECHNOLOGY AREA(S): Human Systems

OBJECTIVE: Develop modular wearable instrument that incorporates real-time sensor and collection technologies for volatiles and aerosols to monitor frequency, magnitude, and chemical make-up of contaminants to understand

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risks to Total Exposure Health (TEH).

DESCRIPTION: The quality of the breathing air has a profound influence on the overall health and ability of individuals to perform duties at an optimal level. Consequently, the presence of contaminants such as environmental gases, volatile organic compounds (VOCs), or aerosols can severely compromise health, primarily by capture within the respiratory tract or in the lungs. These pollutants can cause inflammation of the airway or circulatory system, increasing the potential for stroke or heart attack, or cause headache, dizziness, cancer or neurotoxic effects [1]. Environmental sampling of air quality has demonstrated the presence of airborne contaminants in a variety of settings aside from both anticipated and unexpected exposures in occupational scenarios. The recreational and residential activities of individuals also have unique exposure profiles which contribute to the overall health of the individual, including those caused by vehicular pollution, cleaning products, or cooking [2]. When specific lifestyle choices are taken into consideration, this type of study is referred to as Total Exposure Health (TEH), a complete picture of the exposures a given individual is subjected to in order to perform risk assessment on groups or individuals. In the broad occupational setting of the USAF, an individualized sensor package could be designed specific to the hazards of different careers and TEH choices, tracking exposures over time, and providing toxicologists and Big Data teams with data linked with health outcomes. The long term goal is to use this data to recommend changes to safety procedures, and to ensure personnel are healthy and able to perform at the highest possible level required by the mission.

Wearable sensors provide unique opportunities for TEH, because small battery operated devices are portable enough to travel with an individual and produce a real-time exposure assessment without limiting regular activity throughout the course of an entire day/week/month. One specific application for the USAF environment is for workers such as aircraft fuel tank maintainers, who work in a confined space and hazardous environment with strict air quality monitoring standards. However, this type of technology could be critical for any commercial or USAF occupation requiring hands-free operation, such as maintenance workers, landscapers, laboratory or manufacturing professionals, or machinists. For these reasons, and the fact that the wearable sensing industry has a multi-billion dollar market value only expected to increase in the future, a wearable air quality sensing device represents an interesting platform for TEH sensing.

Airborne contaminants in most environments include both volatile and aerosol constituents, which vary over time [3,4]. Therefore, it is important that airborne contaminants are characterized in high risk environments on a regular basis to guide development and maintenance of engineering controls and personal protection equipment and exposure standards. Currently, a suite of real-time data logging and capturing devices are available for air quality assessments [5]. However, each device requires an independent set of supporting components, including pumps, data loggers and communication ports, making the goal of wearable sensing extremely challenging. Moreover, each device must be calibrated and operated individually by skilled field technicians, and data are pulled from each device independently and are often in different formats. This work seeks to develop a modular wearable air quality device that incorporates real-time sensor and collection technologies for volatiles and aerosols into a single device containing the minimum amount of hardware for successful operation.

PHASE I: Gas-specific chemicals sensed in real-time must include VOCs, CO2, CO, O2, CH2O, NH3, HCN, NOx, H2S, and SO2 at levels below exposure limits, validated by determining cross-sensitivity, limits of detection, and operating range.  Aerosol counts and mass for size cut-offs: 1.0 (including ultrafine), 2.5, 4.0, 10.0 microns. A “bread boarded” benchtop prototype device is acceptable with internal or external data storage and at 6x6x12 in. dimensions, weighing <10 lbs.

PHASE II: The final prototype should weigh <1 lb. with dimensions no larger than 4x4x4 in and include real-time gas-specific sensor and particle counts characterized using temperature (-20ºF-120ºF), humidity (0-100%) and pressure (1-15 psi) conditions in the laboratory and validated in the operational environment. Emphasis is on sensor modularity, and a Graphical User Interface (GUI) that allows for calibration, data collection parameter modification (e.g. logging intervals), data visualization and diagnostics, extensible library, and geographical and spatial location reporting.

PHASE III DUAL USE APPLICATIONS: The vision is a wearable device used to revolutionize exposure assessments by including dynamic description of exposure hazards to assess the TEH profile of an individual to

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mitigate risk scenarios including overall exposure to security forces or aircraft maintainers, with commercial applications in construction or mining industries.

REFERENCES:1. Martin, J. A., Kwak, J., Harshman, S., Chan, K., Fan, M., Geier, B., Grigsby, C., Ott, D. International Journal of Environmental Analytical Chemistry, 2016, DOI:10.1080/03067319.2016.1160384.

2. C. Walgraeve, K. Demeestere, J. Dewulf, K. Van Huffel and H. Van Langenhove, Atmos. Environ. 45, 5828 (2011). doi:10.1016/j.atmosenv.2011.07.007.

3. National Institute for Occupational Safety and Health (NIOSH). NIOSH Pocket Guide to Chemical Hazards.http://www.cdc.gov/niosh/npg/. Last updated Feb 13, 2015. Accessed Feb 29, 2016.

4. Environmental Protection Agency (EPA). NAAQS Table.https://www.epa.gov/criteria-air-pollutants/naaqs-table. Last updated Feb 29, 2016. Accessed Feb 29, 2016.

5. National Institute for Occupational Safety and Health (NIOSH). NIOSH Manual of Analytical Methods.http://www.cdc.gov/niosh/docs/2003-154/method-2000.html. Last updated May 19, 2015. Accessed Feb 29, 2016.

KEYWORDS: Air quality, particulate matter, aerosols, volatile organic compounds, Environmental Health and Safety, exposure limits

AF171-033 TITLE: Mobile activity tracking system for field training and exercise assessment

TECHNOLOGY AREA(S): Human Systems

OBJECTIVE: Develop precise system to track personnel location and activity during indoor and outdoor ground-based training.

DESCRIPTION: Live, virtual, and constructive training (LVC) has brought significant capabilities and cost-savings to the fast jet and JTAC, Joint Tactical Attack Controller, domains. LVC training also has great potential to provide more effective training and cost-savings to ground-based exercises. While fast jet LVC training mainly occurs in a virtual environment, ground-based exercises must occur in the live environment. Thus, a computer system must virtualize the live environment to allow for virtual and constructive injects. Currently, this is difficult to implement due to a lack of precise position tracking capability.

Previous efforts have identified partial solutions to the problem of position tracking within indoor environments using ultra-wide band RFID or close range sonic sensors and within outdoor environments using GPS with smoothing algorithms. These may work in some cases, but to provide ground truth data for a simulation it is imperative that the tracking have a small margin of error. Further, the solutions that are currently available have made it possible to function in either indoor or outdoor, but a common solution that can be utilized during both indoor and outdoor training is desired. Additionally, wearable tracking devices (if any) must be small, lightweight, and long-range. Many current solutions will provide extremely accurate information with close range sensors but a future solution using minimal equipment at long ranges to track an entire exercise is ideal. One last consideration would be ease of installation, the system would ideally be able to be installed quickly with simple calibration and be able to be moved as necessary.

Future development requirements involve using this technology to create extremely accurate positional data for ground entities. The system therefore would need to interface with some kind of DIS, Distributed Interactive

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Simulation, wrapper to create the entities being tracked within the system and provide their information to the rest of the simulation. This data would possibly require some method of adding additional data to certain entities such as firing a weapon to create a munition PDU, Protocol Data Unit, or handling the entity entering a vehicle. This DIS interoperability is a capability that would enable the usage of this technology to its fullest capability. Utilizing DIS interoperability would also provide a common framework to manage the data from a system of this type to create meaningful results. The system should also be capable of using other networks in place to pass the data.

PHASE I: Identify and define the maximum error/tolerance level in personnel tracking that is allowable for DIS protocol. Also identify the accuracy needed to realistically interact with virtual or constructive entities. Design a concept for the method(s) to achieve this accuracy and tolerance in position tracking that is capable of use in both indoor and outdoor training.

PHASE II: Develop, test, and demonstrate a prototype personnel tracking method based on Phase I work. The prototype should track personnel within the defined error level and should be capable of indoor/outdoor use. If wearable tracking solutions are included, they should be small, lightweight, and untethered.

PHASE III DUAL USE APPLICATIONS: Create DIS interoperability software to make the technology accessible to many users. Demonstrate the ability to inject the live players into a DIS simulation for interaction with other entities. Transition the prototype and complete market analysis.

REFERENCES:1. Claire Heininger Schwerin (2011). Army fields next-generation blue force tracking systemhttp://www.army.mil/article/61624/, 2016.

2. IEEE Standard for Distributed Interactive Simulation Applications Protocols, IEEE Standard 1278.1-2012.

3. Reitz, E. A., & Seavey, K. (2014). Distributed Live/Virtual Environments to Improve Joint Fires Performance. Interservice/Industry Training, Simulation, and Education Conference (IITSEC), 2014.

4.Schreiber, B. T., Schroeder, M., & Bennett Jr, W. (2011). Distributed Mission Operations Within-Simulator Training Effectiveness. The International Journal of Aviation Psychology, 21(3), 254-268.

KEYWORDS: immersive training, battlefield airmen, airmen tracking, dismounted tracking, blue force tracking

AF171-034 TITLE: Simulator Common Architecture Requirements and Standards (SCARS)

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

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OBJECTIVE: Develop a benchmark simulator training system architecture that is sustainable in a dynamic cyber security environment.

DESCRIPTION: USAF simulators and training systems managed by the Simulators Division, AFLCMC/WNS, are acquired and sustained to meet user training requirements while also meeting performance standards for concurrency, fidelity, and availability. The ability of a simulator to meet these performance standards in order to provide realistic and reliable training have historically been the primary considerations when awarding a contract to acquire and/or sustain USAF training systems. Emerging, more stringent cyber security requirements are introducing new considerations that now must also be taken into account.

To respond to the new cyber security requirements as outlined in the recent DoD Instructions 8500.01 and 8510.01,Air Force Instruction (AFI) 33-200 and Air Force Manual 33-210, as well as requirements imposed by Authorizing Officials, the Simulator Division is exploring changes in the approach to simulator and training system procurement and sustainment including underlying system architectures. The incorporation of greater modularization and open system architectures hold the promise of enabling simulators and training systems to be more effectively and efficiently procured and sustained in the face of constantly evolving cyber threats.

The Simulator Division is also exploring the concept of "Owning the Technical Baseline" in the form of mandating increased commonality across simulator and training system architectures via the articulation of requirements and standards. These requirements and standards would address system architectures, interfaces and data models. The goal is to develop simulator acquisition specifications in order to reduce technical, schedule and cost risk. The desired result would be more predictable procurement and system sustainment outcomes and costs in a dynamic cyber threat environment.

The current cyber threat environment is forcing simulator and training system updates and modifications to be performed at a higher, recurring rate than previously expected when legacy simulators and training systems were designed and fielded. Evolving cyber security requirements demand simulator and training system architectures which are capable of being modified rapidly to incorporate new security features and eliminate newly identified latent vulnerabilities. The architecture of a simulator or training system impacts the level of regression testing required to confirm system performance has not been adversely affected by a modification undertaken to close a cyber vulnerability.

It is important to understand that the design of high-fidelity real-time simulators involves trade-off decisions between performance, which in the past has often optimized through tightly coupled, natively hosted hardware-software architectures. The sustainment benefits gained via modularity, virtual machine abstraction, reuse, interoperability, and modifiability may be best supported by a different, modular open system architecture approach.

PHASE I: Develop an architecture to meet simulator performance objectives while exhibiting key characteristics of a modular open system architecture. This architecture must enable rapid modification to incorporate new security features, eliminate identified latent vulnerabilities, and minimize or automate the level of regression testing required to confirm system performance has not been adversely affected by a modification, based upon industry "best practices."

PHASE II: Finalize and validate the benchmark simulator architecture developed in Phase I and demonstrate using a notional air crew training simulator application. Demonstrate the architecture exhibits open system architecture characteristics and is modifiable with minimized regression testing.

PHASE III DUAL USE APPLICATIONS: Finalize the architecture for use by the US Government and its contractors for use when developing and upgrading USAF simulators and training systems.

REFERENCES:1. DoD Instruction (DoDI) 8500.01

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2. DoD Instruction (DoDI) 8510.01

3. Air Force Instruction (AFI) 33-200

4. Air Force Manual (AFM) 33-210

5. http://www.acq.osd.mil/dsb/reports/EnhancingAdaptabilityOfUSMilitaryForcesB.pdf

6. https://acc.dau.mil/adl/en-US/631578/file/73333/0SAGuidebook%20v%2011%20final.pdf - Appendix 2,3

7. Manual of Criteria for the Qualification of Flight Simulators -http://123.127.67.21/fagui/ICA09625-AN938 (english).pdf

KEYWORDS: simulator, training system, open system architecture, cyber security, modularity

AF171-035 TITLE: Data Growth Within the Air Force Weather Enterprise

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Reduce impact of expected data growth on the Air Force Weather (AFW) Enterprise by exploring ways of focusing on specific areas of interest for the high-resolution data.

DESCRIPTION: The Air Force Weather (AFW) Enterprise is responsible for providing accurate, timely weather information to the warfighter. It is experiencing large data growth that is stressing its infrastructure and bandwidth capacities. This growth is due to both new sensors and satellites coming online as well as the Enterprise-wide migration to the United Kingdom Met Office (UKMO) weather model. This new model provides data in a much denser resolution than previous models. This, coupled with the fact that weather data is highly perishable, expiring in the matter of seconds for critical information, provides a strong case for weather data needs outstripping the capabilities of the AFW Enterprise infrastructure.

In the past, data growth issues were solved by purchasing more, larger hardware which was then added onto the existing infrastructure. This is not a long-term solution. The Government's analysis predicts that the hardware-only solution will hit a plateau within the next few years, while the amount of data available and needed both continue to rise sharply. Research in the areas of cloud computing and big data have addressed some aspects of this problem but the perishability of weather data has proven to be challenging.

This SBIR is looking to explore ways of ingesting, processing and disseminating high resolution weather data efficiently throughout the enterprise. Areas to consider could include:-Filtering requests and responses for small areas of interest-Optimizing cloud computing for highly perishable data

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-Forward caching techniques to reduce the delays for data requests

PHASE I: Create a study examining the expected data requirements for the AFW Enterprises and identify the projected growth patterns across the next fifteen years. The study will need to take in both existing data sources as well as systems likely to come online. It should look at the existing infrastructure to identify areas for future optimization and analyze possible technical solutions.

PHASE II: Using the study created in Phase I, identify a technical solution(s) to handle the AFW data growth. Create a prototype of the system(s) to ingest, process and disseminate high resolution weather data efficiently across the weather enterprise. The prototype must be built to handle the scale of data identified in Phase I. The final product will be a report detailing the system design and test results of the Phase II prototype.

PHASE III DUAL USE APPLICATIONS: Harden and integrate the Phase II system fully into the AFW Enterprise. Demonstrate the solution in an operation environment at both the present day and expected data loads.

REFERENCES:1.  The Digital Universe in 2020: Big Data, Bigger Digital Shadows, and Biggest Growth in the Farm East -- United States -https://www.emc.com/collateral/analyst-reports/idc-digital-universe-united-states.pdf.

2.  Three Ways Big Data, Supercomputing Changes Weather Forecasting -http://www.informationweek.com/big-data/big-data-analytics/3-ways-big-data-supercomputing-change-weather-forecasting/a/d-id/1269439.

KEYWORDS: cloud, data growth, information technology

AF171-036 TITLE: Energy Efficient Technologies for Tactical Communications and Networking (E2-COMS)

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop highly-efficient power and power conservation technologies for extended ground-to-ground and ground-to-air/air-to-ground battlespace communications.

DESCRIPTION: Energy efficiency is critical to mission success in communication networks involving battery-packed units, such as soldiers served by airborne relays. Subject to size, weight, power and cost (SWAP-C_ requirements, energy efficiency may manifest itself in meting different performance constraints (such as average power or maximum power constraint) or achieving different performance objectives (such as minimizing average energy consumption or maximizing the unit or network lifetime). Without feasible energy-efficient solutions, users with poor channels, high interference/jamming or traffic congestion levels will quickly fail with depleted battery and put the entire mission in danger.

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Energy is spent by radios for different functionalities, such as data transmission and processing, user interfaces, all-weather operations; and by different components, such as amplifiers, antennas, processing units, displays, and embedded Global Positioning System (GPS) receivers. A good understanding of how tactical radios should spend their limited energy (batteries) in the most-effective way is still missing from general battlespace use. Reliable energy profiling of tactical radios is needed to determine the design space for energy-efficient solutions across the entire protocol-stack (including diverse capabilities ranging from power control to energy-efficient routing and transmission control protocols). Dynamic capabilities of switching between sleep/awake modes as part of battery management are also needed to extend the batter-packed unit lifetime while maintaining mission-critical applications without any performance drop. This paradigm involves joint design of energy-efficient solutions with other objectives such as throughput and delay.

Another aspect of energy-efficient operation is how to replenish the unit's battery or how to share stored power among multiple devices. Energy harvesting from nature (such as using solar cells) and wireless energy transfer may answer some of these needs by taking into account SWaP-C requirements. The latest technologies bring new dimensions to system design in the form of randomness and intermittency of available energy, as well as energy storage capacity and processing complexity, all of which call for novel information processing and protocol design.

This topic seeks innovative technologies that provide energy efficient solutions to increase lifetime of tactical communications with improved data rates. The following areas are of particular interest for this solicitation: 1. Modeling energy profile and quantifying it with range experiments; 2. Designing energy-efficient protocols at PHY, Medium Access Control (MAC)/link, network and higher layers in a coherent architecture driven by radio energy profile, SWaP-C and network constraints, and mission requirements; 3. Developing battery management technologies including sleep/awake cycles, to reduce energy consumption at idle times without risking emergent radio communication needs--often communicating on scheduled times which may be updated while in sleep or low-use mode; 4. Developing energy refill technologies to sustain continuous operation of batter-packed units, to include very-rapid recharging; 5. Implementing energy-efficient technologies in real radio environment6. Experimental evaluation of energy efficient implementations that quantify the actual gains achievable with real radios in a high fidelity emulation environment.

Offerors are welcome to address the problem holistically from as many directions as they choose to maximize overall energy efficiency. Also, proposed solutions may be functions entirely of the ground tactical radios, may work cooperatively with other elements of the tactical communications architecture (e.g. network protocols that would need to be present in both ground and airborne nodes to maximize energy efficiency), or a combination of both.

PHASE I: Generate the system design of multiple energy-efficient technologies that can significantly improve energy usage and unit/network lifetime for ground-to-ground and ground-to-air tactical communications. Quantify the benefits using analysis and simulation, accounting for practical implementation constraints. Explore solutions using new ideas. Suggest means to bring to reality in Phase II.

PHASE II: Implement the technology in multiple hardware environments and demonstrate the gains with actual radio elements. Model software-define radios to alter energy use for most efficiency. Present a path toward optimizing SWaP-C. Include both procedural, tactical, and technical, and technical means to extend conservation of power. Account for determining critical need for deviation under battlefield conditions.

PHASE III DUAL USE APPLICATIONS: Demonstrate fieldable long-endurance radio systems in relevant environment. Provide comprehensive training and technology changes for substantial power conservation measures. The energy-efficient communication and networking technologies can benefit the commercial telecommunications world.

REFERENCES:

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1.  D. Gunduz, K. Stamatio, N. Michelusi, and M. Zorzi, "Designing Intelligent Energy Harvesting Communication Systems," IEEE Communications Magazine, Vol: 52, Pages: 210-216, 2014.

2.  O. Ozel, K. Shahzad and S. Ulkus, "Optimal Energy Allocation for Energy Harvesting Transmitters with Hybrid Energy Storage and Processing Cost," IEEE Trans. on Signal Processing, June 2014.

3.  L. Liu, R. Zhang and K-C. Chua, "Wireless information transfer with opportunistic energy harvesting," IEEE Trans. on Wireless Communications, January 2013.

4.  R. Jurdak, A.G. Ruzzelli, and G. MP O'Hare. "Radio sleep mode optimization in wireless sensor networks," IEEE Transactions on Mobile Computing, 2010.

KEYWORDS: energy efficient, energy profiling, power, radio, battery, SWAP-C, experimentation, conservation

AF171-037 TITLE: Mission Assured Authentication (MAA)

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Provide war fighter with the ability to confirm distant end communicator (person/device) is the intended person/device with whom the warfighter is communicating. If not, render the distant node inoperative and/or disconnected from the aerial network.

DESCRIPTION: Control of an encrypted or non-encrypted communications device, whether used for voice, text, or data communications, may find itself outside the control of the U.S. or its allies authorized to employ the device, possibly falling in the hands of the adversary before the assigned user has an opportunity to render the device useless. This could lead to potential compromise of the device, or worse, the network upon which the device is running.

There may be many proposed solutions which have both advantages and disadvantages in this situation. For example, a biometrically actuated (e.g., retina scan, palm print, fingerprint, etc.) device may prevent use of the communications by a legitimate or alternate ad hoc user, including a rescuer of the original owner. Within a tactical squad or flight, use of voiceprinting for all members of the squad may make the device non-interchangeable among the members, thus countering the exclusive use of the device for an assigned user. Perhaps, employment of very-proximate RFID technology to trigger authentication would be one of many considerations.

Various roles, such as a Joint Target Area Controller (JTAC), will have more or less severe effects if the assigned communications device is compromised. Also, there are matters of managing and preparing devices for field use, effect of power (battery) swaps on the device's ability to manage identity, and related issues.

Existing techniques are used by the Armed Forces to work around such issues (e.g., word of the day, verbal authentication using code phrases), which are well known and practiced today. However, as war fighters become

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connected and networked via wireless communications, and as more communications are digital vs. legacy voice, personally-recognized characteristics of the conversation are lost. This is especially true as digital voice often masks or loses personally-recognizable qualities (e.g., tone, timbre, inflection), as well as with text and data communications which rely on other forms of platform-to-platform authentication. These techniques may increase the chance of misuse of a device which could improperly direct fire or be used to lure friendlies into harm's way.

PHASE I: Provide list of know considerations, binned into technical, behavioral, and other means, ensuring distant user identities are confirmed. Provide demonstration of minimum of 5 technical and, at least 5 behavioral means to ensure identity of distant end communicators. Provide 5 demonstrable means to render the danger to minimal or none, citing affordability and practicality of the solutions.

PHASE II: Demonstrate technical solutions on existing tactical communications systems employing voice, text chat, full-motion video, web services, and file transfer. Demonstrate/prove to a 1% or less chance behavioral solutions will not impact war fighter's ability to perform primary mission (e.g., direct eyes away from targets, involve motions and repositioning of hands from the trigger to the communications device, etc.).

PHASE III DUAL USE APPLICATIONS: Engage with radio manufacturers for incorporation of mission assured authentication (MAA) into current and to-be-developed software defined radios. Work with HNAA and HNCE to derive approval path for certification.

REFERENCES:1. Pathak, Manas, et al. "Privacy-Preserving Speaker Authentication." Information Security Conference (INESC). 2012, Lisbon, Portugal.

2.  Cagalj, Mario, et al. "On the Usability of Secure Association of Wireless Devices Based on Distance Bounding." Cryptology and Network Security Conference (CANS). 2009, Kanazawa, Japan.

3.  Chen, Xinyi, et al. "User Authentication Mechanism Based on Secure Positioning System in RFID Communication". Ubiquitous Information Technologies and Applications (CUTE). 2013. Danang, Vietnam.

KEYWORDS: MAA, biometrics, mission assurance, authentication, zeroize, encryption, RFID, word of the day, password, authentication code

AF171-038 TITLE: High-Throughput High-Frequency (HTHF) Battle Management Command-Control (BMC2)

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Utilizing High-Throughput High-Frequency (HF) or "next generation" HF advanced communications, provide innovative nuclear command-control-communications and global strike C2 and situation awareness (SA);

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enhance oceanic flight following and tracking.

DESCRIPTION: High-throughput HF (HTHF) communications equipment can now, achieve throughput rates exceeding 100 kbps, provide reliable digital data transmissions, while still retaining traditional analog voice communications, but without the difficult to decipher audio plagued by static, nearby frequency usage, and competing distortion. Relied upon for today's transmission of emergency action messages (EAM) for nuclear command-control communications (NC3) and overwater international flight navigation and flight following by international military and civil air traffic control (ATC). HTHF greatly enhances robust and reliable communications without need for costly per-byte subscriptions for satellite communications. These dramatic improvements in HF communications now offer NC3 and international traffic, including military airlift and global strike assets, a totally-new environment for situation awareness, reporting, information exchange and dissemination, potentially allowing full awareness of destination changes of mission order changes from 100-6,000 nautical miles (nm).

While many tools or applications exist to support SA and C2, they are, for the most part, geared to higher Ethernet-quality local or wide area net (LAN/WAN) networks. HTHF, operating at still (but much improved) relatively low data rate or throughput speeds, require applications to support intermittent, wireless, and sometimes degraded communications rates, but still thousands of times faster than required for tradition EAMs and coded messages.

We are seeking innovative solutions to provide BMC2 and NC3 in the improved HTHF environment for global mobility, global strike, and strategic military missions. In addition, operating with overseas flight following, tracking, and air traffic control, develop approaches to utilize the 100-200 Kbps communications environment. Develop solutions for multiple-and single-hop HTHF communications. Develop solutions for HTHF propagation prediction and performance enhancement based on current conditions sensed at endpoints of current and recent-past communications exchanges. Incorporate accepted accelerator solutions for certain data types (e.g., XML) to take maximum advantage of limited throughput, perhaps achieving 2x to 50x acceleration rates of HTHF communications. Perform the modeling and simulation (M&S) necessary to verify and validate the performance of the developed solutions.

PHASE I: Provide demo of efficient and effective BMC2, NC3, and ATC apps utilizing low-speed HF comm speeds. Provide recommended approach(es) to interfacing with HTHF system. Address security approaches and develop proposed architecture that would ensure secure passing of sensitive or classified information. Verify and validate performance w/M&S.

PHASE II: Develop approved Technology Transition Plan (TTP) for Phase III activities. Provide robust demonstration and test of, at least, 5 separate BMC2 applications adjusted/invented for next-generation high-throughput HF, and 3 situation awareness (SA) tools. Develop and execute test plan for long-distance communications within US states and territories at appropriate facilities; provide feedback loop using approved circuits.

PHASE III DUAL USE APPLICATIONS: Execute ways ahead outlined in Phase II TTP. Incorporate success BMC2 and situation awareness (SA) applications on target platforms, including air and surface. Provide robust testing of selected applications in operationally-relevant environment.

REFERENCES:1.  Eric E. Johnson, Erik Koski, William N. Furman, Mark Jorgenson, John Nieto, "Third Generation and Wideband HF Communications," Artech House, Norwood MA, 2013.

2. STANAG 5066. "Profile for High Frequency (HF) Radio Data Communications." Edition 3 (Ratification Request), North Atlantic Treaty Organization, 2010.

3.  STANAG 4538: "Technical Specifications To Ensure Interoperability Of An Automatic Radio Control System For HF Communication Links". Edition 1, North Atlantic Treaty Organization, 2009.

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4.  William N. Furman, Eric Koski, John W. Nieto, "Design and System Implications of a Family of Wideband HF Data Waveforms",www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA584160, 2010.

5.  Jeffery Weston, Wric Koski, "High Frequency Radio Network Simulation Using OMNeTT++", Proceedings of the OMNET++ Community Summit 2015.

6.  J. Nieto, "Coding and Interleaving Options for Wideband HF Waveforms", The Nordic Shortwave Conference HF10, Faro, Sweden, 2010.www.nordichf.org.

KEYWORDS: ATC, NC3, HTHF, HF, BMC2, C3, C2, high frequency, application, command-control, command-control-communications, nuclear command control communications, winlink

AF171-039 TITLE: Data Protection and Sharing Technologies In Critical Key Networks and for Cyber Defense of Weapons (DPSTICK)

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop efficient data protection and sharing technologies for Airborne Networks.

DESCRIPTION: Airborne networks are envisioned as an infrastructure consisting of IP-based airborne nodes and on board platforms which provide interconnectivity between terrestrial and space networks forming Global Information Grid (GIG). In Joint Aerial Layer Network (JALN) vision, the airborne network augments and extends the existing aerial layer networks and supports operations in permissive, contested as well as anti-access environments against both kinetic and non-kinetic threats. The airborne networks will be critical assets to transport mission critical information and data at the right place and the right time.

Air Force weapons are increasingly vulnerable to cyber intrusion as apertures, data links, embedded digital processing and other components increase the potential attack surface available to adversaries. The AF desires development of defensive cyber technologies that will detect, deter and eliminate hostile cyber intrusions into weapons and weapon networks. Technology proposals are sought which will leverage recent advances in high assurance of software, vulnerability analysis, provable security, or other techniques to develop weapon-centric defensive cyber solutions.

To achieve reliable data and information sharing among highly dynamic network nodes in hostile environments, effective and secure data distribution and sharing technologies are highly desired. Recent analyses suggest a reliable, secure data and information sharing is currently lacking and that the new technologies are necessary to fill the specific capability gaps.

Most commercial solutions for data storage and sharing technologies are not directly applicable to the airborne networks because of their limited capabilities and their unique characteristics. The airborne network consists of highly dynamic airborne nodes with heterogeneous capabilities, often highly specialized, such as ISR, planning,

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command and control, storage. Node mobility often results in significant network dynamics such as intermittent connectivity which in turn results in continuously changing network topology and changing routes to the information of interest. Moreover, necessary information and data may not be accessible if the information source leaves the network or if the communication links to the node are disrupted. Another deficiency in commercial networks is that the network nodes are not trusted and secured because they can be captured and compromised.

This topic seeks innovative technologies to improve data availability, security and accessibility for the airborne networks. The anticipated solutions should possess the following capabilities: 1) high data availability: data can be recovered when a minimized of network nodes are available; 2) securing data-at-rest: the data stored in network are secured even when a small number of storage nodes are compromised; 3) Adapting to network dynamics: the solutions should accommodate network dynamics to make available the data to users most of the time. The solutions should adapt to network dynamics such as network splitting, merging and node leaving; and 4) low storage and communication overheads. The solutions should incur low communications and storage overhead.

PHASE I: Generate a system design of the data storage and sharing methodologies for airborne networks that can protect data at rest (DAR) and data in transit. Quantify the benefits using analysis and simulations, accounting for practical implementation constraints.

PHASE II: Implement the technology in a hardware environment and demonstrate the gains with actual radio elements. Present a path towards a mature system design. Develop a Technology Transition plan (TTP) for commercialization, government agency use and military applicability.

PHASE III DUAL USE APPLICATIONS: Demonstrate a field-ready data storage and sharing system in relevant environment. Execute TTP.

REFERENCES:1.  Chairman Joint Chiefs of Staff, "Joint Concept for Command and Control of the Joint Aerial layer Network, " 20 March 2015 (Distribution A--Public Release) (http://www.dtic.mil/doctrine/concepts/joint_concepts/joint_concept_aerial_layer_network.pdf) (see p. 2 and p. 7)

2.  T. Schug, C. Dee, N. Harshman, R. Merrell, Air Force aerial layer networking transformation initiatives, IEEE Military Communications Conference, Nov. 2011

3.  D.H. Webster, "Extending the Ground Force Network: Aerial Layer Networking, 25 Apr 2013, http://www.dtic.mil/dtic/tr/fulltext/u2/a602564.pdf

KEYWORDS: airborne networks, data protection and sharing, data-at-rest. data in transit, DAR, aerial, cloud, networked weapons, weapons cyber security

AF171-040 TITLE: Aerial Cloud Analytics for Strategic and Tactical Warfighting (ACAST)

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US

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Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Provide responsive information to conventional and strategic warriors at the tactical edge, and to the planners and decision makers governing the conduct of critical air and surface warfare operations. Develop data analytics tools and techniques.

DESCRIPTION: Cloud operations, comprising data ingress and information egress for critical combat operations, involves smart data analytics to provide the most-effective strategic and tactical battle management command control (BMC2) communications. Aerial Cloud Analytics for Strategic and Tactical Warfighting (ACAST) seeks solutions to smartly ingest and analyze and compile data from multiple sources, in multiple forms, and in both small and massive data content, such as imagery, sensor data, and unmanned aerial systems. This must be accomplished quickly and unambiguously to ensure rapid (near-real time) dissemination via egress mechanisms to appropriate combatant, command-control, and intelligence and mission analysts.

In most cases, some data are received by the intended receiver, most-often in native form, such as a Link-16 track, because the receiver is in the battle space arena; however, this information is local and doesn't enjoy the broader dissemination for increased mission effectiveness. Associated information on that track is not presented, nor is sensor data that would typically flow through the ISR center possessing the most-current data related to that track or target. In the commercial world, Google or Amazon, for example, often can predict what user/consumer wants as they begin typing a query. Airborne battle managers aboard BMC2 platforms have huge amounts of data available to them, but lack the data analytics engines to process the data. Even when an experience mission crew member intuitively understands the information to be passed to a tactical or strategic strike aircrew, formatting those instructions may differ from platform to platform. This is a function of the data analytics engine, as well as the ingress and egress engines.

After data ingress, (big) data analytics engines capable of learning and determining end-user format and information needs are not available, even in the larger command centers--certainly not within the aerial battlespaces. DISA and the Services are working to provide analysis of large data sets, first target at the terrestrial IT and planning infrastructure, but current tools are severely lacking for the warrior on the tactical edge.

Certain commercial industries and think tanks have tools constructed to meet their needs. ACAST will begin to move "big data" analysis to the edge by analyzing the sources (ingress of data), the destinations (egress of data), and the methods upon which aerial cloud systems operate on the data.

Finally, the egress engine, using many methods, must distribute the information or forward data to appropriate customers. In all three component "engines" (ingress, data analytics, egress), adaptability, ability to operate with imperfect data sets, and ability to meet information delivery need and schedules is critical. Like the "OODA" loop, data analytics with appropriate analysis rules and not limited by size of data, will ensure the end-user has the information in the form he or she needs it. Likewise, feedback loops from the destination(s) will inform the ingress and data analytics engines as experience is learned and effectiveness is learned.

PHASE I: Provide demonstrable and customizable data analytics approach employing at least 10 different "ingress" input types (delivered at different speeds, formats, waveforms, origins), at least 10 different "egress" outputs (able to deliver at the fastest speed and in the best formats) for the intended receivers). Consider both rule and context-driven approach.

PHASE II: Develop Technology Transition Plan (TTP) for advancement beyond Phase II. Utilizing both unclassified and sensitive but unclassified data, construct or employ available data center resources (considering airborne cloud limitations, throughput, transient nodes, etc.) to demonstrate a 50-node (virtual) environment (include) surface, aerial, data centers, operations centers, and related entities; provide analysis of pros and cons for various configurations. Provide 2 BMC2 applications.

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PHASE III DUAL USE APPLICATIONS: Identify early employment of data analytics rules and functions. Integrate with appropriate civil, government or military, or commercial data analytics systems.

REFERENCES:1.  Big Data Working Group. "Big data analytics for security intelligence.: Cloud Security Alliance (2013)

2.  Dittrich, Jens, and Jorge-Arnulfo QuianA-Ruiz. "Efficient big data processing Hadoop MapReduce." Proceedings of the VLDB Endowment 5.12 (2012): 2014-2015

3.  Wu, Xindong, et at. "Data mining with big data." Knowledge and Data Engineering, IEEE Transactions on 26.1 (2014): 97-107.

4.  Alvaro A Cardenas, Pratyusa K. Manadhata, Sreeranga P. Rajan, "Big Data Analytics for Security," IEEE Security & Privacy, vol. 11, no. 6, pp. 74-76, Nov.-Dec. 2013, doi:10.1109/MSP.2013.138.

5.  CSAF, "USAF Combat Cloud Operating Concept," 9 Mar 2016.

KEYWORDS: big data, cloud, aerial cloud, combat cloud, airborne, tactical cloud, fusion engine, fusion, analytics, data analytics, cloud security, TCRI,ISR Combat Cloud, data analytics, Tactical Cloud Reference Implementation.

AF171-041 TITLE: Aerial Cloud Computing Technologies (ACCT)

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop technologies to enable aerial tactical cloud capable of in-mission processing and storage of large data using computing resources distributed across multiple aerial platforms and surface platforms (e.g., ships and ground vehicles)

DESCRIPTION: Manned and unmanned aircraft associated with a mission package will contain a myriad of sensors of various kinds. (e.g., video cameras, RF sensors gathering electronic intelligence (ELINT)). In addition to their primary use as real-time ISR feeds, the data collected by these sensors could be fed to analytics tools for generating valuable activity based intelligence (ABI). Such automated and continuous analysis of data could, for instance, yield patterns of behavior of the red forces enabling blue force units to shape and re-shape their tactics rapidly to ensure mission success.

Traditionally, the analytics tools reside at a facility located in the rear-echelons hundreds or thousands of miles from the forward data collection points. The volume of the collected sensor data that will need to be transported from the tactical edge to such a facility could be in the order of hundreds of gigabits per second if one were to just consider wide area motion imagery (WAMI) and RF data alone. These data rates are well beyond what can be supported by BLOS reach-back links now or in the foreseeable future. Hence, data analytics must be performed on computing

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platforms on the tactical edge of the aerial battlefield network. What is needed, therefore, is a cloud computing environment which automatically marshals and orchestrates the existing computing resources embedded within the forward deployed aerial platforms (and potentially surface platforms) to meet the needs of data analytics applications on an on-demand basis.

Aerial Cloud Computing Technologies (ACCT)- enabled capabilities of interest to the Air Force include: 1. A mission-configurable, heterogeneous, intra-aircraft computing cluster (i.e., aircraft-embedded data center) shared by multiple concurrently executing data analytic applications belonging to different security domains (e.g., UNCLASSIFIED, CLASSIFIED). The compute cluster must be elastic, i.e., be capable of being reconfigured on demand during a mission to accommodate changes in the application mix in a agile fashion. 2. Self-forming, self-healing inter-aircraft cloud computing ensemble where processing resources may dynamically join and leave the aerial network. This ad hoc aerial cloud must (1) enable the sharing of information across different aircraft; (2) marshal the compute and storage resources distributed across multiple aircraft to execute data analytics applications belonging to different security domains.3. Mission-oriented cloud manager for monitoring and controlling the operation of the aerial cloud.

The Air Force desires open (non-proprietary) technologies for an agile aerial tactical cloud. Specifically excluded are proprietary protocols, interfaces and other solution artifacts that may inhibit a multi-vender marketplace for ACCT products. Furthermore, information assurance and cyber security requirements for tactical environments must be addressed by any proposed ACCT solution.

PHASE I: Develop the detailed design of an Aerial Cloud Computing Technologies (ACCT) product and demonstrate its implementation feasibility through a proof-of-concept prototype.

PHASE II: Develop a TRL 6 implementation of the ACCT product along with a transition plan for fielding and commercialization.

PHASE III DUAL USE APPLICATIONS: Insert ACCT product within Air Force programs such as Long-Range Strike Bomber (LRS-B), Joint STARS Recapitalization, AWACS modernization, Joint Aerial Layer Network (JALN), and Combat Cloud (CC).

REFERENCES:1. DoD Cloud Way Forward,http://iase.disa.mil/Documents/dodciomemo_w-attachment_cloudwayforwardreport-20141106.pdf.

2. CJCS General Martin Dempsey, USA, "Joint Concept for Command and Control of the Joint Aerial Layer Network," 15 March 2015) Distribution A-Public Release).

KEYWORDS: tactical cloud, aerial layer network, cloud computing, ad hoc networks, domain separation, multiple security levels, combat cloud, tactical cloud reference implementation, TCRI

AF171-042 TITLE: Big Data Cyber Analytics

TECHNOLOGY AREA(S): Information Systems

OBJECTIVE: Develop log-based Big Data cyber analytics that reveal anomalous behaviors in networks.

DESCRIPTION: Today's networks are vulnerable to a myriad of external and internal threats. Conventional network sensors like Firewalls and Intrusion Protection Systems (IPS) are insufficient for detecting low-and-slow attack behaviors and preventing exploitation. New automated non-signature based detection approaches are needed that

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can reveal anomalous behaviors from huge volumes of network sensor log data.

The Defense Information Services Agency (DISA) is developing a Joint Big Data Platform (BDP) based on Hadoop technologies with the intention of collecting, ingesting, storing, processing, and querying huge volumes of network sensor logs. The BDP is expected to be a common platform that the individual DoD services develop advanced analytics upon. A wide and evolving set of analytics are expected to be developed to support a diverse set of use-cases across intel, network operations, defense, and offensive organizations.

Cyber analytics is a rich research area that promises to provide meaningful and actionable knowledge from log data produced by a variety of devices including web proxies, firewalls, IPSs directory servers, and end hosts. This solicitation requests the design and development of Big Data analytics that reveal anomalous behaviors in networks. These anomalous behaviors include, but are not limited to: data exfiltration, lateral movement, exploitation, attacker command and control, credential compromise, denial or degradation of services, and infrastructure performance changes.

Though the initial commercialization is toward DISA the contractor must also show, through specific examples that the analytic can be adapted to non-military industry.

PHASE I: Develop analytic to operate on a Big Data cluster to uncover one or more anomalous behaviors. Identify log messages and fields required for the analytic, and the specific output created. Demonstrate operation of the analytic and results produced. Deliverables include a plan for migrating and testing analytic on DISA's Joint Big Data Platform and identify existing AF log sources to be used. The contractor must show that the performance of the analytic should be able to handle initial data clusters of a billion logs with scaling toward a trillion logs.

PHASE II: Migrate the previously developed to work on top of a DISA BDP cluster. Develop a test harness to produce > 100TB of representative AF log data and ingest the log data into the BDP cluster. Demonstrate the operation of the analytic at scale on the BDP cluster. Required Phase II Deliverables include a test report showing effectiveness of the analytic in terms of probability of false positives and false negatives.

PHASE III DUAL USE APPLICATIONS: Analytics that provide increased situational awareness into cyber defensive posture or insight into performance issues within AF networks will be of use to the larger Joint community. Analytic algorithms can be applied to all DoD and government networks.

REFERENCES:1.  "Big Data Analytics", http://www-01.ibm.com/software/data/infosphere/hadoop/what-is-big-data-analytics.html, retrieved 8 April 2016, webpage.

2.  "By 2016, 25 Percent of Large Global Companies Will Have Adopted Big Data Analytics For At Least One Security or Fraud Detection Use Case", http://www.gartner.com/newsroom/id/2663015, retrieved 8 April 2016, webpage.

3. "Leveraging Big Data for Security Analytics", http://hortonworks.com/blog/leveraging-big-data-for-security-analytics/, retrieved 8 April 2016, webpage.

4.  "Big Data Platform (BDP) and Cyber Situational Awareness Analytic Capabilities (CSAAC)"; DISA; Daniel V. Bart; DISA Infrastructure Development, Cyber Situational Awareness and Analytics; http://www.disa.mil/~/media/Files/DISA/News/Conference/2016/AFCEA

KEYWORDS: Cyber, Big Data, Threats, Analytics, Anomalies, Exploitation, Detection

AF171-043 TITLE: Mobile User Objective System (MUOS) for Moderate Data Rate Communications

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(MMDR)

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Provide means to port MUOS waveform for receive only and transmit-receive in multiple aerial platforms; develop/modify BMC2 and SA applications to support employment by strategic and tactical users.

DESCRIPTION: MUOS is the cross-over replacement and enhancement to the legacy UHF Follow-On (UFO) SATCOM system constellation. MUOS will eventually replace the 16 UFO with 5 MUOS platforms with 4 Radio Access Facility (RAF) ground entry point sites. MUOS is a JTRS waveform which recently completed the MUOS Risk Reduction Effort (MRRE) employing a C-17 and other assets, operating 1 or more of 16 satellite "beams" with data rates of 64 Kbps.

MUOS offers the war fighter greater coverage in the upper latitudes than UFO, employs significantly-faster throughput, permitting continuous access by critical users on assigned missions.

This topic seeks innovative ways to fully utilize MUOS within the aerial layer network, both as a connector and as a data transport medium to including critical C2 data within the Internet Protocol (IP) aerial layer network stream. Requires modernized Tactical Battle Management C2 (BMC2) and Situation Awareness (SA) applications to utilize the unique capabilities of MUOS, especially in high latitude navigation, reporting, and status checking.

PHASE I: Generate the design of porting a new waveform to various existing or in-development software-defined radio (SDR) devices and sharing the content with other essential elements of the IP network for situation awareness, command control, and other time-critical functions for strategic and tactical users. Investigate porting of waveform to selected current military tactical radio system(s).

PHASE II: Demonstrate porting of MUOS to a minimum of two other military radio systems using information supplied through the MUOS information repository. Demonstrate interoperability and use of all three (or more) systems in a relevant operational environment, one of which is aerial layer network platform. Develop or modify BMC2 and SA applications and user interfaces for minimal training, maximum ease of use to fit mission needs. Develop Transition Plan for fielding.

PHASE III DUAL USE APPLICATIONS: Provide approach to modification of other radio systems. Ensure rapid insertion of MUOS capability to UHF capable radios.

REFERENCES:1. DAMIR, "Mobile User Objective System (MUOS) Selected Acquisition Report," 18 Mar 2015, Defense Acquisition Management Information Retrieval, RCS: DD-A&T(Q&A)823-345

2. US Navy, PMW-146-D-10-0041, "Mobile User Objective System (MUOS) Communications-on-the-Move (COTM): 28 April 2009.

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3. Cheah, Jonathon. "Contributions to MUOS Communication Link Assessments at the Arctic Circle Locations." Proceedings - IEEE Military Communications Conference MILCOM 2015 (2015): 187-192.

4. Ramlall, Sunil. "An Automated Framework for Testing MUOS Voice Calls." AUTOTESTCON (Proceedings) 2015 (2015): 329-333.

KEYWORDS: MUOS, SATCOM, Tactical Radio, MRRE, UFO, 64kbps

AF171-044 TITLE: Mobile Authentication and Access Capability

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: To simplify and strengthen the Battlefield Airman Operations Kit authentication and authorization procedures in order to enable rapid and reliable access to combat critical information.

DESCRIPTION: The Battlefield Airman Operations Kit (BAO Kit, BAO Kit-G) is a ruggedized, wearable command and control system designed to support dismounted troops in Air Force operations. The current identification, authentication, and authorization procedures involved with the BAO Kit are manual, complex, and time consuming. More specifically, the system requires multiple manual identification and authentication steps in order for operators to gain access into the system and manage the various software applications and/or hardware interfaces. These system administrative requirements have the potential to distract operators and delay their response to time critical combat tasks. This research effort seeks to address this issue by minimizing the time and steps needed for a user to identify and authenticate with the system.

Simplified identification, authorization, and authentication technologies and methodologies are needed for the operator to perform their tasks and manage multiple hardware and software applications across a system-of-systems mobile computing and communication configuration. Additionally, a rapid response "wake up and operate" capability to mission applications is essential for special operations missions. Rapid access and use of JTAC networks are also needed. These resulting simplified procedures and improved information access capabilities will improve operator situational awareness as well as combat effectiveness while maintaining compliance with Air Force security regulations and procedures.

Battlefield Airmen need to securely access enterprise wide data sources. including multi-level security systems and environments, in order to fulfill their mission needs. New authentication technologies (some examples include: biometrics, RFID, QR codes, etc.), as well as already existing commercial and DoD applications, should be researched and evaluated for usability in a realistic battlefield environment. In addition to these authentication technologies, various authorization and access control methodologies, including, but not limited to, Role Based Access Control (RBAC), Attribute Based Access Control (ABAC), and Proximity Based Access Control (PBAC), should also be investigated and evaluated in this same type of environment.

Lastly, performers on this SBIR effort must identify their own subject matter experts in order to determine the

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existing and currently deployed communications architectures that are utilized by the BAO Kit. These architectures should be assumed for this project. Any solutions developed as a result of this research effort should be compatible with both cabled and wirelessly networked systems. Preferably, the solution should also be platform and operating system agnostic.

PHASE I: Investigate current BAO Kit systems and authentication mechanisms. Research and identify an optimal authentication and authorization approach that works with Android and Windows Operating systems that enables rapid and secure system access. Design a secure enterprise access capability for mobile users. Demonstrate proof of concept using simulated or material components. Document and report findings.

PHASE II: Refine the system architecture to include several users, interacting with each other, with simultaneous enterprise access and information sharing. Evaluate the scalability and system robustness to real-work communication and other real-world constraints. Demonstrate successful multi-user and multi-system network operation.

PHASE III DUAL USE APPLICATIONS: Refine design based on outcomes of tests and customer feedback in Phase II. Obtain necessary certifications and transition capability to militarily useful platforms. Provide finalized operator and maintainer manuals. Develop cost and schedule estimates for full rate production.

REFERENCES:1.  Black Diamond Wearable Modular Tactical System Chosen by USAF for Dismounted Close Air Support, http://soldiersystems.net/2012/07/09/black-diamond-wearable-modular-tactical-system-chosen-usaf-dismounted-close-air-support/

2. Digitally Aided Close Air Support,http://www.specops-dhp.com/interesting-post/digitally-aided-close-air-support-2/

KEYWORDS: Mobile devices, Authentication, Authorizaiton, Battlefield Management, BAOKit, Battlespace Awareness.

AF171-045 TITLE: Automatic Dependent Surveillance - Broadcast (ADS-B) and UAS operations

TECHNOLOGY AREA(S): Air Platform

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a cost effective approach to enable the safe and effective incorporation of UAV operations within the National Airspace System (NAS) while leveraging advancements made under the Federal Aviation Administration's (FAA) 2020 mandate for ADS-B transmission capability.

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DESCRIPTION: Aircraft must be equipped with ADS-B equipment to operate within national airspace after 2020 in the US, Europe, Canada, and Australia. The mandate which applies to US FAA for the National Airspace System (NAS) is listed in 14 Code of Federal Regulations (CFR) 91.225 [1]. The selected venders will develop a cost effective approach to facilitate viable Unmanned Aerial System operations within the mandated ADS-B environment for 2020. The solution needs to incorporate safe and effective use of UAVs within the aviation environment.

PHASE I: Analyze current technology and conduct a feasibility study for a system that will enable optimal use of UAVs within the FAA 2020 ADS-B mandated environment with a cost effective and secure solution. Result will include at a minimum completion of a top level conceptual design, defining the optimal way ahead to implement the design and submission of a complete report.

PHASE II: Implement, demonstrate, and deliver prototype system as designed in Phase I with consideration for flight safety, airworthiness and platform specifics to ensure broadest adoption within aviation community (government and commercial user bases). Use of known standards encouraged to best minimize disruption and to incorporate secure operational performance.

PHASE III DUAL USE APPLICATIONS: Integrate new technology to enable combined UAS and military aircraft while exploring the use of technology adoption for commercial aircraft fleets. Transition to provide a viable solution in the incorporation of UAVs within the 2020 ADS-B mandated environment.

REFERENCES:1.  14 Code of Federal Regulations (CFR) 91.225 [1]

2.  An Approach to Assess the Safety of ADS-B-based Unmanned Aerial Systems: Data Integrity as a Safety Issue / Authors: Daniel Baraldi Sesso, Lucio F. Vismari, Antonio Vieira da Silva Neto, Paulo S. Cugnasca, Joao B. Camargo Jr., Published - 2014 International Conference of Unmanned Aircraft Systems. (ICUAS), IEEE, Date 21-30 May 2014 Site:http://ieeexplore.ieee.org/xpl/login.jsp?tp=&arnumber=6842311&url=http%3A%2F%2Fieeexplore.ieee.org%2Fxpls%2Fabs_all.jsp%3Farnumber%3D6842311

3.  Optimization-Based Path Planning for Separation Assurance on Small Unmanned Aircraft / Authors: Matthew Duffield, Andrew Ningy, Timothy McLainz., American Institute of Aeronautics and Astronautics AIAA InfoTech Aerospace. San Diego, California 4-8 Ja

KEYWORDS: Air Traffic Control, Automatic Dependent Surveillance Broadcast, ADS-B, FAA, Next Gen, Air Transportation System, Unmanned Aerial Systems, aviation

AF171-046 TITLE: 3rd Party Intellectual Property (I V&V Effort)

TECHNOLOGY AREA(S): Nuclear Technology

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon,

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gail.nyikon@us.af.mil.

OBJECTIVE: Prototype a 3rd Party Intellectual Property verification and validation software system against a UART or similar complexity IP block. This effort will develop and evaluate an innovative software system for the V&V of a discrete IP block.

DESCRIPTION: As the US Government upgrades its current nuclear deterrent systems, acquisition/sustainment organizations (AFNWC, SSP) increasingly employ modern microelectronics. To reduce cost, microelectronic designers procure 3rd Party Intellectual Property, often of unknown pedigree, which raises trust and reliability concerns. This SBIR will develop and evaluate an innovative software system for independent V&V that the 3rd Party IP performs as specified, with no unexpected or undesirable functionality. While a UART or similar complexity IP block is identified as a potential target, any IP block of similar complexity can be used for the development and demonstration of these techniques (see www.opencores.org). Methodologies and techniques developed should meet performance characteristics:1) Compatibility with standard Electronic Design Automation (EDA) tools to the greatest extent possible, including:

a. Cadence "Incisive Formal Verifier"b. Mentor Graphics "QuestaR Formal Verification Apps"c. Synopsys "VC Formal, VC LP and Spyglass"2) Scalable to larger, more complex IP blocks and number of IP blocks across the SoC 3. Minimization of manual analysis steps4. Process metrics that demonstrate the depth and nature of the IP V&V process, including number or percentage of logic discrete blocks identified, number or percentage of functions mapped to identified blocks, confidence of mapping, number of percentage of unknown functions identified, etc.Methodologies and techniques developed must comply with all 3rd Party IP terms of use.

PHASE I: Develop 3rd Party IP V&V concept design against UART or similar IP. Develop initial demonstration of new & innovative techniques for IP V&V. Focus on development of mechanisms, robustness & processes required. Performers need to consider scalability to more complex and IP blocks of varying function during initial concept phase. Initial demonstration does not need to be a fully automated process.

PHASE II: Develop automated prototype 3rd Party IP V&V software system against UART or similar IP demonstrating robustness and scalability of the solution. The PHASE I process will be refined & test cases of "modified" IP will be provided for evaluation of the evolving tool set. These test cases will represent undesirable modifications to the IP to evaluate robustness & provide the development team areas where improvement is needed. Different IP blocks will be introduced for evaluation to develop a versatile tool that will be effective for evaluation of any IP block.

PHASE III DUAL USE APPLICATIONS: US Gov't procurement organizations validate/verify that UART or similar IP do not contain malware. Development will be refined for transition to program designers & government V&V teams. This will include a user friendly GUI and evaluation of multiple IP blocks of varying complexity.

REFERENCES:1. "Using 3rd Party IP in ASIC/Soc Design," Mohit Gupta,http://www.design-reuse.com/articles/31313/using-3rd-party-ip-in-asic-soc-design.html.

2. "Redefining Chip Complexity in the Soc Era." Ramesh Dewangan, April 3, 2014,http://www.realintent.com/real-talk/1052/redefining-chip-complexity-in-the-soc-era.

3. "Does an externally bought IP need re-verification?" Anand Shirahatti, May 2014,http://www.arrowdevices.com/blog/does-an-externally-bought-ip-need-re-verification/.

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4. "Exponentially Rising Costs Will Bring Changes," Pete Singer, January 26, 2015,http://electroiq.com/petes-posts/2015/01/26/exponentially-rising-costs-will-bring-changes.

KEYWORDS: Microelectronics, 3rd Party IP, UART, IP Verification

AF171-047 TITLE: Resilient Communications for Contested Autonomous Manned/Unmanned Teaming

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop communications capabilities for next generation platforms to perform manned/unmanned teaming operations with semi autonomous for C2, flight control, shared situational awareness, extended sensor/electronic warfare/communications, targeting, and employment of weapons.

DESCRIPTION: Unmanned operations require bandwidth that can vary for a variety of reasons, including different mission phases, different geographic locations and attenuation of signals (both intentional and unintentional). Types of information to be passed over the link will include route way points. mission objectives, targeting commands, sensor data, etc. Vehicle mission environment will be a mix of multiple manned and unmanned aircrafts.

To maximize the use of finite resources and make the systems more resilient, a communications capability that monitors behavior and dynamically allocates communication resources in a multiple UAV mission environment is needed. The solution should be designed to interface with piloted aircraft.

Current technology often builds upon basic concepts like quality of service and solutions are desired that provide more robustness, flexibility and higher performance.

Development should be focused on enabling applications to utilize existing and evolving standards for both multiple unmanned vehicle control and mission management. The desired solution should be able to automatically react to changes in connectivity by both prioritizing and optimizing the data being transmitted within the operational context of the supported unmanned vehicles. The solution should also automatically transmit previously established prioritized information in varying restricted environments. Methods could involve reduced frequency of transmission, reducing the type and/or fields of data transmitted, or other techniques that would allow reactivity to the variability of link conditions.

PHASE I: Develop an initial design and prove feasibility of a   communications capability that monitors behavior and dynamically allocates/reallocates resources to optimize critical messages in a multiple UAV mission environment.

PHASE II: Develop a prototype based on Phase I effort using conceptual techniques and demonstrate in a relevant simulated environment.

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PHASE III DUAL USE APPLICATIONS: Finalize, operationally test and transition solution to a program of record.

REFERENCES:1. Third Offset Strategy, Deputy Secretary of Defense Bob Work, 14 Dec 15, Center for a New American Security, Washington, D.C. Retrieved   from   http://www.defense.gov/News-Article-View/Article/634115/dod-extends-technological-operational-edge-into-the-future.

2. Howard, C.(2013). UAV Command, Control and Communication.Military and Aerospace Electronics,Volume 24(7). Retrieved from  http://www.militaryaerospace.com/articles/print/volume-24/issue-7/special-report/uav-command-control-communications.html.

3. Stansbury, R. S.. Vyas. M. A.,& Wilson, T. A. (2009). A Survey of UAS Technologies for Command, Control, and Communication (C3).Journal of Intelligent and Robotic Systems.Volume 54(1-3),61-78.

4. USAF Strategic Master Plan 2015, Page 59;Vector: Continue the Pursuit of Game-Changing Technologies; Retrieved fromhttp://www.af.mil/Portals/1/documents/Force%20Management/Strategic_Master_Plan.pdf.

5. Autonomous Horizons, System Autonomy in the Air Force -A Path to the Future, Volume I: Human-Autonomy Teaming, AF/ST TR 15-01 June 2015 Retrieved fromhttp://www.af.mil/Portals/1/documents/SECAF/AutonomousHorizons.pdf? timestamp=1435068339702 .

KEYWORDS: Autonomous communications, resilient communications, access-denied communications, adaptive communications, shared situational awareness, command and control

AF171-048 TITLE: Big Data Analytics for Activity Based Intelligence

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Overcome the Big Data challenges of analyzing multi-int data to enable scalable analytics for Activity Based Intelligence.

DESCRIPTION: The number, variety and fidelity of sensors continue to increase yielding increasingly complex analytical challenges. Activity-based intelligence (ABI) has emerged as a new intelligence methodology aimed at exploiting this opportunity. The Under Secretary of Defense for Intelligence defines ABI as or "a multi-INT approach to activity and transactional data analysis to resolve unknowns, develop object and network knowledge, and drive collection." [1] Fundamentally, ABI is a discipline of intelligence where analysis and subsequent collection are focused on the activity and transactions associated with an entity, population, or area of interest "in decision advantage." While ABI has emerged within the IC, another shift has occurred within technology that creates the opportunity to realize the benefits currently obscured by the variety, volume, and velocity of the data.

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Open source Big Data technology now enables the storage, retrieval, analysis and exploitation of data for which traditional data processing applications were inadequate. The details and aims of Big Data technologies vary, however the unifying theme tends to be the usage of commodity hardware and parallel computing. In addition, open source Big Data technologies are increasingly creating an ecosystem in which a variety of technologies build upon each other or work well together. Hadoop [2] and Spark [3] present new opportunities in batch analytics while systems like Samza [4] and Storm [5] tackle unwieldy data streams. In addition, generic architectures like the Lambda Architecture [6] have emerged that seek to combine Big Data technologies to enable scalable and fault-tolerant data processing architectures.

Unfortunately, the full potential of big data technologies has yet to be realized with regard to ABI and the processing of geospatial activity and transactions. Typically, algorithmic advances with ABI applications have been developed within traditional data processing architectures. In addition, Big Data technologies are often utilized for basic storage and retrieval, or very basic statistics. This SBIR aims to develop advanced analytics within Big Data architectures to produce a game changing capability to understand and act on activity and transactional multi-INT data from a variety of different sources. The only agreed upon notion of what constitutes Big Data is data sets that are so large or complex that traditional data processing applications are inadequate. The one of the appealing aspects of solutions provided within Big Data architectures is the potential to achieve horizontal scalability so the solution may be scaled up or down as necessary. In addition to transforming intelligence, and the ways in which people intermingle and interact with the physical and virtual world.

PHASE I: Develop novel algorithms utilizing Big Data technology to discover relevant patterns, determine and identify change, and\or detect and analyze trends within multi-int data. Evaluate the performance and viability of these methods using realistic data sets (simulated or collected) (demonstrate feasibility)

PHASE II: Implement algorithm prototypes in a realistic environment that enables thorough testing of algorithms. Incorporate applications to support testing, e.g., operator displays, decision support systems. Demonstrate and validate algorithm(s) effectiveness. Deliver an algorithm description document, engineering code and test cases. Explore and document other potential methodologies identified in Phase I.

PHASE III DUAL USE APPLICATIONS: DUAL USE APPLICATIONS: Develop and mature the technology for use within the DoD, Intelligence Community, and Homeland Security as well as other viable commercial applications (marketing, business intelligence, cyber security...).

REFERENCES:1.  C. P. Atwood, "Activity-Base Intelligence: Revolutionizing Military Intelligence Analysis." 01 April 2015. [Online]. Available:http://ndupress.ndu.edu/Media/News/NewsArticleView/tabid/7849/Article/581866/jfq-77-activity-based-intelligence-revolutionizing-military-intelligence-analys.aspx. [Accessed 20 04 2016].

2. "Apache Hadoop, [Online}. Available:http://hadoop.apache.org/. [Accessed 20 04 2016].

3. "Apache Spark,"[Online]. Available:http://spark.apache.org/. [Accessed 20 04 2016].

4.  "Samza," [Online]. Available:http://samza.apache.org/.   [Accessed 20 04 2016].

5. "Storm." [Online]. Available:http://storm.apache.org/. [Accessed 20 04 2016].

6.  "Lambda Architecture." [Online]. Available:http://lambda-architecture.net/. [Accessed 20 04 2016].

KEYWORDS: Activity Based Intelligence, Big Data, Analytics

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AF171-049 TITLE: Collective Human Intelligence as Exploitation Layer in Automated Information Systems

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop collaborative/collective intelligence system where human interaction is independent but cooperative with autonomous analytics for information exploitation.

DESCRIPTION: The analyst community faces ever-increasing volume of data products from numerous data sources. The ISR community is relying heavily on improvements to machine analytics. However, one of the challenges to machine analytics is the reliance on historical data and to adapt to the dynamic nature of human decision-making. New scenarios or events often calls for centralized organizations to use subject matter experts (SME) to create new processes or techniques. The SME faces the daunting task of reaching out to other experts and singularly judging the credibility of their analysis.

The product ranking in Amazon may be considered collaborative filtering [1,2). Similarly, the ISR community could rank the quality of data, refer products to peers and even propose alternative uses for information in other mission areas.

Another suitable use of collaborative intelligence is to break "stovepipes" and reduce bureaucratic inter-agency overhead. Rather than conduct collaboration within organizations, on-line communities could emerge over areas of expertise. In this way, a seismologist working on earthquakes could collaborate with a seismologist working on nuclear treaty monitoring.

The focus of this topic is to implement commercial success in collaborative intelligence for information exploitation. The concept goes beyond human-in-the-loop techniques but puts the human component as neither superior or inferior to the machine component.

Collaborative intelligence will serve as a powerful tool to address the challenges of understanding human interaction. For instance, in 1999, Microsoft sponsored a chess match between Garry Kasparov and volunteers around the world. Kasparov, considered the leading chess player in the world played a game against 50,000 people in 75 countries in a game of chess. Ultimately, the ''world" lost but Kasparov considered it one of the most complex games in history [3]. The world players also had coaches in the game which would be analogous to the SMEs in their respective fields.

PHASE I: Identify commercial and government social and collaborative intelligence processes for use within the ISR community. Determine solutions to obstacles in implementing such solutions for the DoD and IC communities.

PHASE II: Implement technologies identified in Phase I and integrate within current mission systems. Assess the value of such technologies in the decision making process.

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PHASE III DUAL USE APPLICATIONS: Targeted technologies will transition to AFRL, 25AF and other DoD partners. They will be incorporated into the ISR PED and US Government cloud infrastructure.

REFERENCES:1.  Adomavicius G. and Tuzhilin, A., "Toward the next generation of recommender systems: a survey of the state-of-the-art and possible extensions," in IEEE Transactions on Knowledge and Data Engineering, vol. 17, no. 6, pp. 734-749, June 2005.

2.  Long-Zhen, W. Gui-Fen and R. Yan, "Collaborative Filtering with Improved Item Prediction Approach for Enhancing the Accuracy of Recommendation, "2012 Fourth International Conference on Multimedia Information Networking and Security, Nanjing, 2012, pp. 349-352.

3.  Marko, P. and Haworth, G. M. (1999) The Kasparov-World Match. ICGA Journal, 22 (4) pp. 236-238.

KEYWORDS: Collaborative intelligence, collective intelligence, multi-source, multi-int, machine learning.

AF171-050 TITLE: Human-Machine Collaboration for Automated Patterns of Life Analysis

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a fully interactive system that encourages human-machine collaboration for Patterns of Life analysis over multi-modal data.

DESCRIPTION: Automated pattern recognition and predictive analytics technologies have emerged to help intelligence analysts more efficiently process large streams of multi-INT data feeds. However, automated solutions still provide only limited value. For example, while development of annotation and benchmark datasets [5] has advanced large-scale single-image scene classification and object detection models, state of the art computer vision algorithms can only detect the objects they are well trained on, and still produce detection rates much lower than humans [4]. Even with existence of annotated imagery datasets, the fully supervised learning is inefficient, and semi-supervised learning have been developed. Further, video-based activity recognition algorithms can't assume the presence of large training datasets due to manpower requirements in annotating videos [3], and recently focused on semi-supervised learning from sparse set of example [2] to improve classification accuracy. Recently, a significant interest of the computer vision community is on enabling collaboration between humans and machines in producing better classification performance [5].

All-source analysts are faced with even greater challenge: they need to combine data from different modalities, and the types of "useful" results depend highly on the types of tasks that analysts have. Consequently, development of tools for multi-source multi-modal fusion has to account for the ever changing needs of the analysts, and hence must be adaptive to the needs of the users. Learning patterns of life in multi-source multi-model domains, and especially in Anti-Access Areas of Denial (A2AD) environments [1], is akin to discovering "unknown unknowns". But how can automated information fusion algorithms discover such patterns? Drawing on the advances achieved in

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computer vision, we hypothesize that semi-supervised multi-int learning algorithms that use supporting concept libraries (Ye et al., 2015) and interactively engage the human analysts may facilitate the technology development in this area.

The focus of this topic solicitation is to create a full user-in-the-loop feedback system that encourages the analysts to provide expert guidance in patterns of life specification. Solutions are needed that leverage minimal inputs from humans to help multi-int fusion algorithms develop models that are tailored to the analyst's preferences, the characteristics of the data and domain specific knowledge. Such a system may have algorithmic core that can learn patterns from large volumes of unlabeled training data in unsupervised manner, present representative candidates to the analysts to validate and annotate, and incorporate their feedback in semi-supervised manner to re-label and re-structure the resulting patterns. The user-should be able to provide corrections to annotations as well as patterns of life that automated solution develops, as well as define their own patterns re-using the information provided by other users or algorithms as "building blocks". Overtime, the pattern library is populated with highly-accurate, user-vetted patterns which are tailored to the user, INT type, data source and analysis task.

Solutions of interest will be focused on implementing the user-in-the-loop feedback system described above. Novel methods for online-learning of patterns of life from incremental, multi-source, multi-INT data streams are encouraged. The proposed solution burdensome on the human but maximally valuable to the machine. The solution must be able to accommodate dynamic patterns of life and conflicting observations in the input data.

PHASE I: Using representative open source data of at least two modalities (e.g. vision or text), develop and demonstrate a set of algorithms that learn patterns of life and accept user-provided corrections. Techniques should be able to process noisy data and demonstrate scalability. Demonstrate a proof-of-concept to AFRL.

PHASE II: Using online-streaming multi-INT, multi-source data, develop and demonstrate a set of algorithms with the Enhanced Exploitation and Analysis Tools (E2AT) environment located at AFRL/RRS All Source Process and Exploitation (APEX) Center that would provide rapid learning and re-learning of patterns of life using analyst feedback. Techniques should demonstrate improvements over state-of-the-art processing. Demonstrate a robust proof-of-concept with the E2AT environment.

PHASE III DUAL USE APPLICATIONS: Targeted technologies would be to transition to matured AFRL E2AT, NASIC, and PCPAD-X programs. Any application, whether military or commercial, requires methods and capabilities to develop and learn pattern of life indicators and hot to apply to analysis of customer requirements.

REFERENCES:1.  Gao, J.; Ling, Haibin; Blasch, Erik; Pham, Khanh; Wang, Zhonghai; Chen, Genshe. "Pattern of Life from WAMI Objects Tracking based on Context-Aware Tracking and Information Network Models". Retrieved 23 May 2013.

2.  Misra, I., Shrivastava, A., & Herbert, M. (2015). Watch and Learn: Semi-Supervised Learning for Object Detectors From Video. In Proceedings of the IEEE Conference on Computer Vision and Pattern Recognition (pp. 3593-3602).

3.  Oh, S., Hoogs, A., Perera, A., Cuntoor, N., Chen C. C., Lee, J. T., ... & Swears, E. (2011, June). A large-scale benchmark dataset for event recognition in surveillance video. In Computer Vision and pattern Recognition (CVPR), 2011 IEEE Conference on

4.  Borji, A., & Itti, L. (2014, June). Human vs. computer in scene and object recognition. In Computer Vision and Pattern Recognition (CVPR), 2014 IEEE Conference on (pp. 113-120). IEEE

5.  Russakovsky, O., Li, L. J., & Fei-Fei, L. (2015). Best of both worlds; human-machine collaboration for object annotation. In Proceedings of the IEEE Conference on Computer Vision and Pattern Recognition (pp. 2121-2131).

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6. G Ye, Y Li, H Xu, D Liu, SF Chang (2015). Eventnet: A large scale structured concept library for complex event detection in video. MM'15 Proceedings of the 23rd ACM international conference on multimedia, pages 471-480

KEYWORDS: machine learning, POL, pattern of life, anomaly, track, multi-int fusion, A2AD, automated patterns, multi-modal data

AF171-051 TITLE: Elevated Situational Awareness through Discovery and Characterization of Composable Free Market Analytics

TECHNOLOGY AREA(S): Information Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a modular, secure solution for analytics across multiple domains to be autonomously represented, characterized, and discovered for bandwidth-optimized summarization, transfer, evaluation, and tasking.

DESCRIPTION: DoD Situational Awareness (SA) has evolved from simple translation of information between operational domains to SA transference involving mission effects and impacts, role-based relevancy metrics, big-data predictions for prioritization, and complex event analysis. However, while the raw information has become more interoperable, discoverable, and sharable, the analytics through which domains interpret them have not. Not only are analytical tasks not portable, policy-negotiable, or interoperable between domains, but it is not feasible to transfer large datasets between communities with disparate bandwidth and connectivity in order to perform domain-specific analysis.

Analytical tools have become siloes just as data repositories used to be. However, while database standards have emerged for characterization, metadata, transaction processing, queries, and discovery, analytics engines and analysis tools have not. Unfortunately, this limits the scope and power of many advanced features that could be enabled through the orchestration and management of analytics across multiple toolsets and mission domains.

Just as operational situations are ever evolving, analytical approaches that could increase mission effectiveness over time should create robust technologies that are empowered with support for evolution, re-use, and orchestration. One means to empower mission and domain transferable analytics is by enabling a shared, discoverable representation of their requirements, injection formats, results, and provenance. The resulting technology would provide an analytics "free market" system that enables higher level analysis, optimized usage of multiple best-of-breed analytic engines, and more effectively match analytical resources with mission needs by profiling and capturing metrics for available analytical tools.

Developing such capabilities requires addressing several challenges, including:

- Characterization and discovery of analytical operations that represent and span multiple domains and toolsets.- Higher level analytics decision making, management, and orchestration controls. - Assurance for analytics tasking and translation

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The expected results of this effort include strategies and approaches to successfully implementing distributed analytics orchestration, creating an interoperable understanding of available data analytics resources, and enterprise-level methods for discovery and collaboration. It also results in a foundation that enables a level playing field by allowing analytical tools to be evaluated in a more 1-to-1 manner, a layer of abstraction for feedback and qualitative analysis to occur, and for best-of-breed analytics to continue to live in their own ideal element, while also contributing to a higher level analytics ecosphere.

PHASE I: Design a prototype system that leverages/fuses multiple analytics engines as part of flexible architecture of discovery, access, and cross-tasking. The representation and optimization of analytics resources should be formed with the above objective in mind.

PHASE II: Development of a prototype system that implements the Phase I design, and demonstrates/validates the prototypes performance using representative mission and information analytics.

PHASE III DUAL USE APPLICATIONS: The resulting system will support SA and general purpose analytics, which have both military and commercial applications.

REFERENCES:1.  Sakliker, Samir (2013). Sharing Threat Intelligence Analytics for Collaborative Attack Analysis. RSA Conference.

2.  Ransbotham, Sam (2015). Data at the Heart of the Sharing Economy. MIT Sloan Management Review.

3.  Johnson, John (2016). High Performance Computing for Intensive Science. Pacific Northwest Laboratory.

4.  Office of Technology Strategies (2016). VA Enterprise Design Patterns: Interoperability and Data Sharing, Enterprise Data Analytics.

KEYWORDS: situational awareness, mission awareness, distributed machine learning, information fusion, information management and discovery, cross-domain solutions

AF171-052 TITLE: Non Intrusive Passive Optics/Imaging for Damage Prediction and Structural Health Monitoring in Gas Turbines

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop conceptual approaches that assess component degradation, flaws, and anomalies; the approaches use advanced sensors and image analysis that overcome current nondestructive inspection (NDI) limitations with real-time optical and electromagnetic sensors and algorithms.

DESCRIPTION: A significant challenge in aerospace engine and airframe structural inspection is in how to reduce manpower and provide repeatable accuracy. The increasing use of composite materials and integrated components such as blisks add to the technical challenge and point to the need for development of a reliable accurate non-intrusive rapid inspection capabilities.

Current state-of-the-art (SOA) aircraft and engine structural inspections are done using electromagnetic sensors (eddy current), ultrasound, and penetrant dye (FPI) techniques. These techniques are labor intensive (over 100 hours per module), are low volume, and often do not have consistent accuracy (5-mil flaws). Hot and cold section turbine blades are discarded due to poor cost of inspection versus replacement. More automated inspection techniques, such

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as acoustic thermography and scanning electromagnetic probes, are maturing; however, the problem is the time required to perform these inspections is a linear function of the area that the sensor can cover in time and is a serious limitation of these techniques for integrated rotor inspections. Limitations of current optical near infrared (NIR) imaging inspection are also related to labor, efficiency, and capability.

Significant developments in the field of hyperspectral (HSI) and hyper temporal (HTI) imaging algorithms and hardware have occurred over the last 10 years. They have historically been applied to environmental, surveillance, and other remote sensing problems. These techniques which apply wide spectrum imaging sensors can currently be leveraged to damage assessment of aircraft and engine structural components. HSI/HTI is accomplished by collecting spectral band data at the pixel level or through spatial light modulation over time. Passive sensors, such as cameras with ambient illumination are often used for image generation. The data sets obtained can provide a complete inspection record from the images scanned. The ability to inspect a wide array of aerospace structural components using HSI/HTI with passive optics of an image of arbitrary size has benefits over current optical visible and infrared (IR) techniques. Application of spectral and temporal image processing offer significant capability improvements to aircraft and engine health management at the engine depot or repair facility. They will also augment current methods in use.

The SBIR program should address development of an innovative image-based inspection capability that has the potential to replace FPI, reduce use of eddy current by 50 percent, accommodate component dimensioning, and increase parts inspected per unit time over 2X. Image inspection advances NDI technology by capturing all relevant surface data of complex parts or multiple parts in a single array for processing, compared to low rate, high cost individual component area inspection. Development of new algorithms that reduce dimensionality and increase ability to find hidden flaws in the data at high rates compared to visual and scanning NDI techniques. The effort should leverage SOA sensors and imaging components while applying new algorithms that perform data separation and intelligent processing that can assess the structural integrity of aerospace structures and components (detection of flaws, material artifacts). SOA wide spectrum imaging hardware may be considered for this application. Technology such as cameras, optics, digital array sensors, excitation sources, and mechanical controls for HSI can be leveraged to achieve this capability. Comparison of the results with baseline SOA methods should be accomplished to establish a measure of improvement in both capability and inspection time. Working with an engine or airframe vendor is recommended to enhance the relevance and transition ability of the final research product.

PHASE I: Apply new NDI methodology to relevant rotor NDT image data collected by an engine original equipment manufacturer (OEM) or depot. Demonstrate the feasibility of the algorithms using collected spectral image data to the detection of flaws in integrally bladed rotors (IBRs). Demonstrate the potential to achieve on-line analysis and high levels of confidence for small features on complex parts compared with SOA penetrant and eddy current.

PHASE II: Develop a fully functional HSI/HTI component imaging capability, including data collection methodology and software algorithms. Select a relevant engine turbine component, such as an IBR to demonstrate the capability. Compare the accuracy and probability of detection (POD)/confidence levels achieved with SOA dye penetrant and electromagnetic methodology. Develop a preliminary transition plan and business case analysis.

PHASE III DUAL USE APPLICATIONS: Apply the concepts and capability developed in Phase II to a depot or inspection facility application. Develop an implementable hardware/software and imaging solution for industry use.

REFERENCES:1. “Hyperspectral Imagery Algorithms for the Processing of Multimodal Data, Mohammed Seghir Benmoussat,” Thesis, 19 December 2013, Fresnel Institute, Fraunhoffer IIS.

2. Yong-Kai Zhu, Gui Yun Tian, and Rong-Sheng Lu Hong Zhang, “A Review of Optical NDT Technologies,” Sensors Open Access Journal (MDPI) ISSN, 8 August, 2011, pp. 7773-7798.

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3. Giovanni Maria Carlomagno, “Infrared Thermography in Materials Inspection and Thermo-Fluid Dynamics,” Carosena Meola, University of Naples, Federico II, Italy, 2011.

4. Joseph Zalameda, “Air Coupled Acoustic Thermography Inspection Technique,” NASA Langley Research Center, MS221, Hampton, VA, 2007.

5. Frank O. Clark, Ryan Penny, Jason Cline, Wellesley Pereira, and John Kielkopf, “Passive Optical Detection of a Vibrating Surface,” SPIE, August, 2014.

KEYWORDS: imaging, optical imaging, NDT, inspection, flaw detection, disk crack detection, infrared (IR) thermography

AF171-053 TITLE: Extrapolating Useful Life from Composite Structures Using In-Service Data

TECHNOLOGY AREA(S): Materials/Processes

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Directly mapping full ultrasonic c-scan 3D datasets to 3D models. Identify and size anomalies to allow comparison with previously stored images of the same asset at a previous inspection.

DESCRIPTION: Over the years, much effort has been spent on developing a fundamental understanding of how metallic aircraft structures age through phenomena such as corrosion, fatigue, thermal cycling, impact damage, etc. In contrast, although there has been significant work done to determine how composite structures age in laboratory settings, there is a lack of research in correlating damage in composite structures using actual in-service data. Since composites have not been used in aircraft structures as long as metals, it has been difficult to make any correlations in this area based on actual flight data until recently. The United States Air Force (USAF) has been flying several aircraft that contain substantial percentages of composite structures for over 10 years, so the capability for making these comparisons to improve fleet management is now possible.

Since these aircraft have been in service for long periods of time, they have accumulated a significant amount of data pertaining to their maintenance history to include repairs, replacements and inspections. Furthermore, they have also accrued operational records that detail the number of flights, flight hours, profiles, etc. Typical records for maintenance include nondestructive inspection (NDI) data. The chief subset of that NDI data is based on ultrasound techniques since they are well established and proven for providing insight into the state of composite structures. Ultrasonic c-scan data is collected to identify defects (disbonds, delaminations) and to evaluate the status of indications stemming from repairs and other previously identified items from both the manufacturing and sustainment environments. Ultrasonic c-scan data provides a two dimensional image that can be mapped directly to a 2D drawing or shell model of the article being inspected. This visualization ability enabled by the capability to map c-scan images to models has become a very powerful tool for NDI technicians and structural engineers alike. However, the c-scan image also carries 3D data in the form of greyscale levels in each image pixel that could also be utilized for visualization and analysis purposes.

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The USAF has a need to develop a software capability that directly maps the full ultrasonic c-scan 3D dataset to 3D models to not only provide location of interest, but to also enable depth visualization of indications. The software system must have the capability to identify and size anomalies while the user compares c-scan images with previously stored images of the same asset at prior inspection cycles. This will enable NDI technicians and engineers to identify the growth of disbonds and other defects within the structure. The software must support the capability for USAF personnel to also map and track repairs/replacements to models in a similar way to the c-scan images (area and depth). The software mapping capabilities must also be extended to other NDI modalities, visual inspections (digital photographs), and other maintenance/engineering data to the maximum possible extent. Accurately mapping all this data will provide a better holistic view of the structure. In addition, the software must incorporate analytical features that leverage the image comparisons in order to precisely determine the change of any anomaly or region of interest. Finally, USAF personnel need the ability to enter flight hour, number of flights, and flight profiles, and the USAF users must be able to correlate and extrapolate future states given current c-scan or other maintenance data and known flight operations/profiles.

PHASE I: Develop a software capability that directly maps the full ultrasonic c-scan 3D dataset to 3D models to not only provide location of interest, but to also enable depth visualization of indications. Assess the ability of NDI technicians and engineers to identify growth of disbonds and other defects within the structure with mapped 3D dataset.

PHASE II: Produce and test integrated software tool to automatically map c-scan 3D datasets to 3D models alongside other manually mapped NDI data and tracked repairs/replacements to provide user with full inspection and maintenance picture. Test additional user tools for historical trending and data mining to provide holistic view of the structure.

PHASE III DUAL USE APPLICATIONS: Deploy system for current Air Force military air vehicles that produce c-scan datasets to provide the program office detailed analysis of scan results.

REFERENCES:1.  C. Garnier, M.L. Pastor, F. Eyma, and B. Lorrain, "The detection of aeronautical defects in situ on composite structures using Non Destructive Testing," Composite Structures, pp. 1328-1336, April 2011. http://www.sciencedirect.com/science/article/pii/S0263822310003594

2. G. Steffes, J. Shearer, S. Turek, W. Fong, T. Sharp, and G. Coyan, "Aircraft Management and Sustainment Using NDI Data Trending and Mapping Technologies," 2012 ASIP Conference Proceedings, December 2012.http://www.meetingdata.utcdayton.com/agenda/asip/2012/proceedings/presentations/P6271.pdf

3. N. Brierley, T. Tippetts, and P. Cawley, “Data fusion for automated non-destructive inspection,” Proceedings of the Royal Society A, DOI: 10.1098/rspa.2014.0167, May 2014.http://rspa.royalsocietypublishing.org/content/470/2167/20140167

KEYWORDS: NDI, c-scan, inspection, ultrasonic, disbonds, nondestructive, composite

AF171-054 TITLE: Non-GPS Relative Navigation for Remotely Piloted Aircraft (RPA) Refueling

TECHNOLOGY AREA(S): Air Platform

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type

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of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: This topic is intended to develop relative navigation technology needed for the refueling of remotely piloted aircraft (RPA) in an environment where a GPS signal is unavailable due to signal jamming or satellite disruption.

DESCRIPTION: Most USAF aircraft types have a refueling capability, but USAF RPA are the exceptions. Predators, Reapers, and Global Hawks were designed to be low speed, small payload, long-endurance aircraft that can accomplish their missions without refueling. Future RPAs will likely need speed, stealth, and payloads to achieve their missions and won’t be able to use the long-endurance planforms that the current generation uses. Today, well-trained receiver pilots maintain relative navigation (RelNav) with the tanker using their vision and cues from the air refueling operator. In recent demonstrations, AFRL’s automated aerial refueling (AAR) boom/receptacle and NAVAIR’s Unmanned Combat Air Systems (UCAS) probe/drogue programs demonstrated how differential GPS RelNav systems could guide an RPA to the contact position. Differential GPS was selected for these programs both for the technical maturity of the technique–it had been developed extensively in the late 90s and early 2000s for landing systems and for the safety metrics that could be generated and monitored in real-time. The problem with differential GPS is its dependence on the GPS signal. A tanker/receiver pair could be impacted by local jamming or a disruption in the GPS satellite constellation. A relative navigation solution that is organic to the two aircraft would be preferable, but it would need to produce results comparable to the differential GPS technology.

Electro-optical/infrared (EO/IR) vision systems, laser systems, and datalink ranging have been considered for non-GPS relative navigation, but no system has established itself as the solution to the problem. The Air Force is proposing a SBIR topic for non-GPS RelNav for RPA refueling. The system could be hosted on the tanker, receiver or split across aircraft. Respondents would need to design and develop the proposed system and evaluate the performance in the context of required navigation performance (RNP) metrics. Size, weight, power, communications, antenna and aperture requirements are also relevant in evaluating systems.

Refueling systems have had common interfaces and it would be desirable to keep that true with RPAs.

PHASE I: - Design candidate system- Analyze expected performance in terms of RNP capabilities (accuracy, integrity, availability and continuity)- Discuss tanker and receivers’ data requirements and equipment requirements to include antennas and apertures- Identify any Government-Furnished Information (GFI) that would be required for Phase II.

PHASE II: - Perform laboratory testing with hardware in the loop and simulation- Evaluate RNP capabilities- Evaluate system design and aircraft certification impacts

PHASE III DUAL USE APPLICATIONS: - Conduct flight testing on Air Force and/or surrogate vehicles- Analyze achieved performance

REFERENCES:1. “Automated Aerial Refueling Team Tests Advanced Sensors,”http://www.wpafb.af.mil/News/Article-Display/Article/399478/automated-aerial-refueling-team-tests-advanced-sensors

2. “Fueled in flight: X-47B first to complete autonomous aerial refueling,”http://www.navair.navy.mil/index.cfm?fuseaction=home.NAVAIRNewsStory&id=5880

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3. “Quantifying the performance of navigation systems and standards for assisted-GNSS,”http://www.insidegnss.com/node/769

4. S.M. Calhoun, J. Raquet, and G. Peterson, “Vision-Aided Integrity Monitor for Precision Relative Navigation Systems,” Proceedings of the 2015 International Technical Meeting of The Institute of Navigation, Dana Point, California, January 2015, pp. 756-

5. Thomas, P.R., Bhandari, U., Bullock, S., Richardson, T.S., and Du Bois, J. L., “Advances in air to air refueling,” Progress in Aerospace Sciences, Vol. 71, pp.14-35, 2014.

KEYWORDS: AF, GPS, refueling, tanker, autonomy, autonomous, RPA, UAV, NGT, KC-46

AF171-055 TITLE: Fast High Resolution, High Contrast Microfocus X-Ray Computed Tomography Reconstruction Algorithms for ICBM Components

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop algorithms, software and computer system that eliminate artifacts, enhance image quality and improve speed of microfocus cone-beam computed tomography applied to nondestructive testing of small components in ICBM systems.

DESCRIPTION: Microfocus cone-beam computed tomography (CBCT) is used by the Air Force, for nondestructive testing, to inspect small components of Intercontinental Ballistic Missile (ICBM) systems. The inspections cover a breadth of applications, including verification of reliability, manufacturing defects, stress and aging characterization. Defects, material changes, wear or aging may cause a component to fail. Investigations of the causes of failures and studies into the reliability of systems and devices all warrant microfocus CT inspection. Microfocus CT systems like all CT systems have inherent problems particular to the type of system. Despite the many advantages of microfocus cone beam CT technology, it suffers from artifacts and distortion due to not having a full complement of information for a mathematically accurate inverse.

Sometimes it is difficult to accurately image the axial extremes of a sample because of these issues. Scatter is severe compared to standard CT because collimation is not used. Beam hardening can be severe. Iterative solutions can suffer from long processing times, considering that cone beam datasets and the reconstructed volume are large compared to many standard CT configurations. Solutions to these problems should include innovative software algorithms and computer systems that will push the limits of the visual and 3D information currently provided by microfocus cone beam CT. Advanced scanning geometries, including the helical cone beam geometry, get around many of the problems, but require more complex equipment, scanning, data and time.

This topic seeks innovative solutions which include computer algorithms, software and computer hardware methods that address all of the following limitations: (1) cone beam artifacts, including axial smearing caused by the incomplete data of the cone beam geometry, (2), data truncation, (3), resolving power and magnification limits, (4),

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objects that do not fit in the viewing field, (5), noise d settings, (6), aliasing, (7), Compton scatter, (8), nonlinearities caused by high Z materials, (9), beam hardening, (10), speed of computation, (11), limit in volume size.

PHASE I: Conduct of one or more proof-of-concept tests of promising technologies to accomplish the objective, and develop a plan for g the proof-of-concept into a prototype solution of technologies that are viable candidates for supporting ICBM imaging technologies.

PHASE II: Demonstrate prototype on actual CT images acquired at Hill AFB, UT. This demonstration will show measurable improvements over in 2D and 3D visualization, analysis of CT images and defect evaluation. End of effort: Deliver a final polished prototype with documentation.

PHASE III DUAL USE APPLICATIONS: Military: Focus is ICBM small components. Industrial computed tomography for nondestructive testing is a growing field with a growing market. Commercial: This technology could be used on any industrial cone-beam CT system with the same results. Manufacture of components for aircraft and automobiles.

REFERENCES:1. ASTM E1441-97 (Reapproved 2003), “Standard Guide for Computed Tomography (CT) Imaging” (1997), West Conshohocken, PA.

2. ASTM E1695-95 (Reapproved 2013), “Standard Test Method for Measurement of Computed Tomography (CT) System Performance” (1995), West Conshohocken, PA.

3. ASTM 1570-00 (Reapproved 2011), “Standard Practice for Computed Tomographic (CT) Examination” (2000), West Conshohocken, PA.

KEYWORDS: microfocus computed tomography, nondestructive inspection, artifacts and noise, ICBM components, cone-beam CT images

AF171-056 TITLE: Fiber Optic Sensing Systems (FOSS) for Expendable Launch Vehicles

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Precision FOSS health monitoring system to augment or replace legacy instrumentation systems on expendable launch vehicles.

DESCRIPTION: The Fiber Optic Sensing System (FOSS) technology, under development at NASA, is a pervasive game-changing technology that can benefit multiple SMC programs. The FOSS concept involves sensors capable of being distributed in vast networks that yield an unparalleled amount of real time engineering data - up to 100x the number of measurements for 1/100 of sensor weight. By detecting changes in reflected wavelength from a laser

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source, stress, temperature, deflections, and other measurements can be made at numerous hard to reach locations, embedded into composite structures, and easily installed and calibrated. Other benefits include accuracy, reliability, and immunity to electromagnetic interference (EMI). FOSS has been demonstrated on aircraft test flights but the technology has not been bridged to space systems.

As an alternative to the legacy current/voltage health monitoring systems on EELV launch vehicles, FOSS can provide an order of magnitude more engineering information that can be used for model anchoring, design optimization (e.g., reduction in overly conservative margins leading to reduced weight), and pre/post mission analysis. Benefits also extend to faster design / development cycles, quicker flight anomaly resolution, and greater launch availability.

This solicitation seeks to develop an affordable, reliable FOSS architecture to replace strain gauges, accelerometers, thermocouples, and propellant level sensors for future EELV launch vehicles. Along with the system architecture, the deliverable will include a cost, weight, power and reliability impact assessment.

Technology Need Date: 2023 (EELV Phase III)

PHASE I: Feasibility study on what types of instrumentation and sensors on future expendable/reusable launch vehicles can benefit from FOSS, together with metrics on cost, weight, accuracy, reliability and other engineering or manufacturing benefits.

PHASE II: Subscale demonstration comparing FOSS to legacy current/voltage based health monitoring systems on a representative launch vehicle subsystem (propellant tank, composite skirt, engine nozzle, etc.)

PHASE III DUAL USE APPLICATIONS: Flight demonstration on an EELV launch vehicle validating FOSS capability and benefits. Transition plan for commercial deployment of FOSS to select industries.

REFERENCES:1. Hon Man Chan et al., "Fiber-Optic Sensing System: Overview, Development and Deployment in Flight at NASA," NASA NTRS Technical Report AFRC-E-DAA-TN25056, 10 Dec 2015.

2. F. Pena et al., "Fiber Optic Sensing System (FOSS) Technology: A New Sensor Paradigm for Comprehensive Subsystem Model Validation throughout the Vehicle Life-Cycle," NASA Armstrong Briefing, 26 Oct 2015.

KEYWORDS: FOSS, fiber-optic, instrumentation, sensor, health monitoring, launch vehicle, transducer, measurement, space

AF171-057 TITLE: Dynamic and Efficient Vapor Compressor for Aircraft Thermal Management Systems (TMSs)

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: To develop and demonstrate an approximately 125 to 150 kW nominal capacity, dynamically responsive refrigerant vapor compressor which can sustain high efficiency over a range of turn-downs for next-generation aircraft thermal management systems (TMS).

DESCRIPTION: Aircraft have become thermally constrained such that during specific operating points, thermal requirements can exceed available sinks. This problem has been exacerbated further due to a rise in aircraft mission-related equipment. These challenges have necessitated the development of more efficient and adaptive thermal cycles which can more effectively manage thermal lifts and make better use of available aircraft heat sinks.

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Several strategies for increasing TMS power density and responsiveness have been proposed including development of advanced vapor compression systems (VCS) and hybridization of VCS with conventional air cycle systems (ACS). While these approaches appear viable, highly efficient and power-dense vapor compression options, which can maintain high efficiency over a broad range of inlet and discharge pressures, are limited. The objective of this topic is to develop and test a highly dynamic vapor compressor or compressor/compressor hybrid which demonstrates high efficiency over a range of inlet and discharge pressures. Ideally, oil-less compressor strategies which permit efficient flow turn-downs of as much as 10:1 at a total capacity (mission equipment thermal loads) up to 125 to 150 kW are desired. Specific design objectives include saturated suction temperatures (SST) as low as 1.7 degrees C (35 degrees F) with 2.58 MPa (375 psia) maximum condenser pressure. Also, the compressor must be able to change its capacity (mass flow) at a rate of at least 15 percent per second.

Compressor solutions must be tolerant to 32.2 degrees C (90 degrees F) inlet temperatures. A minimum isentropic efficiency of 0.5 is desired. The primary motivation of this effort is to demonstrate an aviation-grade compressor which minimizes off-design efficiency reductions over the specified turn-down range. However, offerors are encouraged to consider power density (max cooling capacity/compressor mass) as a secondary, but still critical factor in aviation-grade hardware. As such an objective for compressor power density is 8 to 9 kW/kg. Additionally, if possible, the compressor should have no inherent materials incompatibilities with other refrigerants, such as R152a, R236fa, R245fa, etc.

It is anticipated that the compressor to be developed will be electric motor driven. If so, the motor and motor controller design should be considered. Additionally, a model, or compressor maps and dynamic performance data, would be desirable to enable evaluation of the suitability of the compressor for operability within TMS architectures under consideration. While not required, it may be beneficial for the offeror to develop a relationship with a weapons system contractor or subsystem supplier to facilitate transition of successful compressor technology to future architecture demonstrations, and ultimately to future aircraft TMS.

At the conclusion of this activity, AFRL would seek to demonstrate successful compressor concepts as part of ongoing adaptive, next-generation aircraft power and thermal management system technology efforts. As such, delivered hardware may be operated in AFRL’s Vapor Compression System Research Facility (VCSRF) laboratory to verify performance against program desirements.

PHASE I: Design and demonstrate a vapor compressor or hybrid compression configuration which meets the above specifications. A predicted compressor map of the proposed system should be provided to the Government at the conclusion of this effort. Further, the offeror shall demonstrate that they have the necessary facilities and expertise to manufacture a prototype system under Phase II funding.

PHASE II: Refine the design and produce a prototype version of the compressor concept developed under the Phase I. To accommodate Phase II test constraints, a subscale prototype of approximately 75 to 100 kW may be acceptable, though this subscale prototype must still meet desired design requirements. At the conclusion of this effort, the offeror must demonstrate operation of the device through either internal characterization, in conjunction with AFRL’s vapor compression test bed, or both.

PHASE III DUAL USE APPLICATIONS: Commercial applications include aviation-grade cabin-air coolers and related cooling applications. Military applications include advanced thermal management systems for aircraft.

REFERENCES:1.  Ensign, T.R. and Gallman, J.W., "Energy Optimized Equipment System for General Aviation Jets," Proceedings of the 44th AIAA Aerospace Sciences Meeting and Exhibit, January, 2006 (228) doi:10.2514/6.2006-228.

2.  Walters, E.A. and Iden, S., "Invent Modeling, Simulation, Analysis and Optimization," Proceedings of the 48th AIAA Aerospaces Sciences Meeting, January 2010 (287) doi:10.2514/6.2010-287.

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3.  Michalak, T., Emo, S., and Ervin, J., "Control strategy for aircraft vapor compression system operation," Int. J. Refrigeration, Elsevier, Vol 48, December 2014, pp 10-18, doi:10.1016/j.ijrefrig.2014.08.010.

4.  Dexter, P., Watts, R., and Haskin, W., "Vapor Cycle Compressors for Aerospace Vehicle Thermal Management," SAE Technical Paper 901960, 1990, doi:10.4271/901960.

5.  Delash, T., "Vapor Cycle Compressor Range Expansion for Aerospace,” SAE Technical Paper 2011-01-2586, 2011, doi:10.4271/2011-01-2586.

KEYWORDS: aircraft thermal management, aircraft environmental control systems (ECS), vapor compression system (VCS), aircraft cooling

AF171-058 TITLE: Non-Persistent Tracers for Particle Image Velocimetry in High-Mach Number Wind Tunnels

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop a non-persistent nano-scale tracer injection system for particle image velocimetry in high-speed wind tunnels. Particles must have a known finite lifetime, survive and track flow in hypersonic wind tunnels, and accept fluorescent coatings.

DESCRIPTION: The non-intrusive measurement of fluid velocity in wind tunnels depends heavily upon particle-based diagnostics. Particle image velocimetry (PIV) allows for both two- and three-dimensional measurements of the instantaneous velocity field, in which the fluid velocity is approximated by the motion of injected tracer particles [1]. In order to minimize the measurement error associated with particle lag, measurements in supersonic and hypersonic flows typically require a particle diameter d_p between 100 and 200 nm. Additional desired performance characteristics may include low material density (to minimize buoyancy effects), high reflectivity or index of refraction (to maximize scattered laser signal), and the ability to accept fluorescent coatings (to mitigate wall reflections) [2].

Particle injection, whether using liquid aerosols or solid tracers, is typically tolerated in blowdown wind tunnels due to the minimal impact upon facility infrastructure, though increased fouling of vacuum pumps and windows may be experienced. For closed-circuit facilities, the persistent nature of the tracers leads to increased build-up along compressor fans and turning vanes, thus requiring expensive and time-intensive cleaning (if such cleaning is even possible). The development of non-persistent tracers is seen as a possible solution, as the particles would evaporate/sublimate downstream of the measurement location. Early efforts at clean seeding have used dry ice crystals [3], though nominal particle diameters are still too large for regular usage, and the particles are not suitable for injection into the high-temperature settling chambers of hypersonic wind tunnels.

The goal of this effort is to develop a non-persistent PIV seeding system for supersonic and hypersonic wind tunnels. The tracer particles will have a nominal diameter d_p between 100 and 200 nm (as measured in the test region of the flow). Particle lifetime will be short enough to prevent accumulation in wind tunnel infrastructure, and will be sufficiently long to allow particles to convect from the injection location through the test section. Seeding material shall pose no major toxicity danger to personnel, and will not corrode mechanical equipment. Methods and procedures should be provided for applying fluorescent coatings to the non-persistent tracers.

In order to successfully perform the work described in this topic area, offerors may request to utilize unique facilities/equipment in the possession of the U.S. Government located at Arnold Air Force Base during the Phase II effort, including VKF Tunnel D.

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PHASE I: Demonstrate the seeding injection system on a bench-top level, showing the nominal particle diameter d_p < 200 nm. Measurements shall include median particle diameter, along with size distribution. Tracer lifetimes will be appropriate for usage in VKF Tunnel D at Arnold Engineering Development Center (AEDC). The ability of particles to reflect laser light (i.e., for PIV) shall be demonstrated.

PHASE II: Install seeding injection system into VKF Tunnels A or D, for use with government-furnished PIV system. Effectiveness of particles will be demonstrated for various test geometries, including flat plates and wedges. Particle response times will be measured in situ. Particle reflectivity will be compared to traditional persistent tracers (either solid or liquid).

PHASE III DUAL USE APPLICATIONS: Seeding injection system will be further refined for high-temperature applications comparable to those in VKF Tunnel C. Particle survival in high-temperature environments will be demonstrated. Supplementary demonstrations may include particle scattering with and without fluorescent coatings. Possible commercialization applications include customized seeding systems for large-scale and/or closed-loop wind tunnel facilities.

REFERENCES:1. Ragni, D., Schrijer, F., van Oudheusden, B., and Scarano, F., "Particle Tracer Response across Shocks Measured by PIV," Experiments in Fluids 50(1), pp. 53-64 (2011).

2. Petrosky, B., Lowe, K., Danehy, P., Wohl, C., and Tiemsin, P., “Improvements in Laser Flare Removal for Particle Image Velocimetry using Fluorescent Dye-Doped Particles,” Measurement Science and Technology 26(11) (2015).

3. Liber, M.L., Reeder, M., Wolfe, D., Schmit, R., and Hagen, B., “PIV in the Trisonic Gas Dynamics Facility,” AIAA Paper 2014-2661.

KEYWORDS: supersonic, hypersonic, flow diagnostics, particle image velocimetry, particulate, materials, seeding

AF171-059 TITLE: Sustainable High-temperature Hybrid Turbine Rotors

TECHNOLOGY AREA(S): Materials/Processes

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a durable and sustainable joining method for high-temperature hybrid turbine components.

DESCRIPTION: Increasing engine temperatures are expected to present significant thermomechanical challenges for conventionally manufactured turbine disks. This is because the conventional disk alloy, with its fine grain structure, is designed mainly to withstand burst, but is only intended to operate at relatively low secondary flowpath temperatures. Turbine blades, which generally run at the much higher primary flowpath temperatures, are now being made of single-crystal alloys, for improved creep resistance. However, in advanced engines, where the disk rim

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temperatures are coming uncomfortably close to those of the primary flowpath, the disk alloy in this region could undergo adverse grain growth and creep, which when coupled with the high centrifugal forces at the rim, can result in a catastrophic turbine disk failure.

There are a number of ongoing efforts to develop a hybrid disk that will meet both requirements (to be rupture-proof at the bore and creep-resistant at the rim). Currently available joining methods include:1. Linear friction welding: Requires careful alignment of the single crystal orientation at 90° to the bond line; potential degradation of structural properties in the heat affected zone (HAZ); local deformations that will require post-process repairing (if it can even be done)2. Solid state diffusion bonding/welding: The much lower process temperatures (50-90% of the absolute melting point of the parent material) avoid both the HAZ issue and the local deformation, but the process times are quite long (2-3 minutes for the actual joining + a total of 1 to 2 hours for heat-up and cool-down). In practice, because of inevitable surface roughness and also the presence of oxide layers on most faying surfaces, it is not feasible to bring together the surfaces of two pieces within inter-atomic distances, and the necessary metal-to-metal contact cannot be accomplished by simply putting the two pieces next to each other.

The goal is to develop a method for producing a durable high-temperature hybrid turbine disk. The key performance parameters include the ability to produce a clean bond line (no voids, cracks, or local deformations or phase changes), while maintaining the parent materials properties. Anticipated military engine systems benefits include higher OPR driving temperature capabilities to handle high T4 and T3 (longer life with lower cooling) and reduced cooling flows. Anticipated benefits to the warfighter include lower maintenance costs and increased system availability.

PHASE I: Determine the feasibility of producing a durable high-temperature dual-alloy disk. Develop a structural integrity and durability evaluation plan, including both destructive and nondestructive test methods.

PHASE II: Produce two test disks. Use the structural evaluation plan developed in Phase I to assess the structural integrity and mechanical properties of the test disks. Make recommendations for scaling up the process to produce advanced turbine rotors.

PHASE III DUAL USE APPLICATIONS: Potential commercial applications for this technology include military and civil air-, sea-, and land-based propulsion and power generation systems.

REFERENCES:1. http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110020259.pdf.

2. http://www.au.af.mil/au/awc/awcgate/vistas/match8.pdf.

3. http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140000732.pdf.

4.  http://www.omicsgroup.org/journals/review-and-analysis-of-powder-prior-boundary-ppb-formation-in-powder-metallurgy-processes-for-nickelbased-super-alloys-2168-9806-1000127.php?aid=49144.

5. http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120001798.pdf.

KEYWORDS: turbine disk, hybrid disk, dual-alloy disk, turbine rotor, turbine engine, diffusion bonding, linear friction welding, joining techniques, dual-property disk

AF171-060 TITLE: Novel, Tactical-Sized Reconfigurable Aerial Refueling Boom

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TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop a smaller sized aerial refueling boom concept that serves the needs of tactical aircraft, is more easily integrated onto a tanker in a variety of locations, and features novel actuation and control capabilities for robust operation.

DESCRIPTION: Today’s aerial refueling booms are designed to transfer fuel at high rates, and are sized to meet the needs of legacy bomber aircraft and heavy transports. Current and legacy fighters can accept fuel transferred only at an appreciably slower rate, and as such, the current refueling booms are oversized. Tanker aircraft do periodically refuel bomber and mobility aircraft, but the majority of refueling sorties are for fighter aircraft. In looking to the future, as unmanned combat air vehicles (UCAVs) enter the inventory, the demand for refueling of smaller, tactical vehicles will increase. A better match would be a new, smaller boom, appropriately sized for offloading fuel to fighters and UCAVs; it would be easier to integrate onto tankers in a variety of locations (wing mounted, off centerline, on the ramp, etc.), require less powerful actuators to enable the full range of control, and impart lower reactive loads onto the tanker. As the Air Force considers smaller tanker aircraft to meet emerging needs in future environments, there is a unique opportunity to develop a right-sized smaller boom for servicing tactical receivers.

An additional desire is the ability to service both receptacle-equipped receiver aircraft (typical for Air Force aircraft) and probe-equipped aircraft (typical for Naval, rotary wing, coalition aircraft) on the same flight. This is currently done with a centerline-mounted boom and wing-mounted hose and drogue pods; this is standard on existing tankers. There would be great utility in having a multi-mode device that could service both types of receivers on the same sortie.

To aid in integration into the tanker, novel control effectors and mechanisms are sought. Current booms have small wings, which provide aerodynamic forces to steer the boom into different relative positions as the boom operator attempts to connect with the receiver aircraft. These wings are effective, but quite bulky; they create appreciable drag when not in use, and prevent the boom from being stored internally in the tanker. Unconventional control effectors could be examined to understand the strengths and weaknesses in this sort of application. Possible solutions could include, but are not limited to, flow control (pneumatic, mechanical, electrical or otherwise), shape memory alloys, morphing or flexible structures, etc. An additional consideration is the ability of the boom effectors to be effective at generating the required loads across a larger flight envelope, as the Air Force seeks to broaden the range of flight conditions (especially higher altitudes and lower speeds) at which it can conduct aerial refueling. The boom should retain adequate control-margin in aircraft-wakes and in challenging flight conditions. Another useful capability would be to develop a refueling device which is small enough to be mounted to the aircraft externally, and to open up the possibility of buddy refueling or every-aircraft-a-tanker operational concepts.

PHASE I: Product is a conceptual design of a novel boom, sized to meet the needs of tactical receiver aircraft, which is controllable over the range of orientations relative to the tanker, and which is compact and stowable inside the outer mold lines of a tanker or a pod.

PHASE II: Technical substantiation and maturation of the conceptual design, possibly including subscale wind tunnel test to prove the control effector concept; mockups to show the integration, stowage, and actuation; high-fidelity simulation in a realistic flight environment (including for example gusts/wakes), and further detailed system design and systems engineering.

PHASE III DUAL USE APPLICATIONS: Anticipated applications (beyond aerial refueling booms) could include: aircraft primary control effector (for pitch, roll, or yaw control), high lift device, mothership/daughtership aerial retrieval mechanism, or aerial package dispenser.

REFERENCES:1. Bolkcom, Christopher, “Air Force Aerial Refueling Methods: Flying Boom versus Hose-and-Drogue,” Congressional Research Service, 2006. Order code RL32910.

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2. “Air Mobility Planning Factors,” AFPAM10-1403, 2011.

3. Dougherty, Stanley, “Air Refueling: The Cornerstone of Global Reach - Global Power,” Air University Air War College, AU/AWC/RWP076/96-04, 1996.

KEYWORDS: aerial refueling, boom, flow control, hose and drogue, morphing structure, actuation, tactical aircraft, UCAV

AF171-061 TITLE: Micro Reactor Synthesis of Energetic Ionic Liquids

TECHNOLOGY AREA(S): Materials/Processes

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: To develop a safe, low cost and continuously processed energetic ionic liquids and synthesizing the raw materials that are blended together to produce AF-M315E.

DESCRIPTION: Micro reactors, advanced flow glass reactors or miniaturized reaction systems offer many advantages because they have a large surface-to-volume ratio of miniaturized fluid components which allows for significantly enhanced process control and heat management. The resulting large surface-to-area volume ratio reduces or even eliminates heat and mass transfer resistances found in large reactor systems. Other advantages include shorter residence times, increased selectivity and yield. Also, safety and product quality is improved. Micro reactor production is considered a “green chemistry” because the reactors are self-contained with minimal emissions, require few reagents, and generate less waste. Energetic ionic liquids like HEHN and HAN are presently manufactured in batch quantities in chemical reactors that need stringent temperature and quality control measures. The raw materials like HEH and HAFB are toxic, require special handling procedures, and produce large quantities of waste. A micro flow reactor which runs continuously can safely produce production quantities of energetic ionic liquids in a walk-in laboratory hood while minimizing raw materials and waste products.

PHASE I: Develop a continuous processing procedure using micro flow reactor technology to produce the main ingredients that make up AF-M315E which include HEHN and HAN. We are also interested in the continuous flow synthesis of the raw materials that go into making the ionic liquids. The minimum production rate is 2.5 - 5 kg/hr. These materials will meet government and industrial quality specifications.

PHASE II: Refine and demonstrate a safe and robust micro flow reactor process to produce a minimum quantity of 100 kg/hr of AFM315E energetic ionic liquid components and their raw materials. Demonstrate a plan to process energetic ionic liquids using off the shelf micro reactor equipment that can be transitioned to the chemical industry.

PHASE III DUAL USE APPLICATIONS: Dual use application.

REFERENCES:

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1. Current Organic Chemistry, Vol. 9, Issue 8, pp. 765-787 (2005).http://benthamscience.com/journals/current-organic-chemistry/volume/9/issue/8/page/765/

2. Hessel, V. and Löwe, H. “Organic Synthesis with Microstructured Reactors,” Chem. Eng. Technol., 28: pp. 267–284. doi:10.1002/ceat.200407167 (2005).

3. Watts, P. and Haswell, S. J., “The Application of Microreactors for Small Scale Organic Synthesis,” Chem. Eng.Technol., 28: pp. 290–301. doi:10.1002/ceat.200407124 (2005).

4. Roberge, D. M., Ducry, L., Bieler, N., Cretton, P., and Zimmermann, B., “Microreactor Technology: ARevolution for the Fine Chemical and Pharmaceutical Industries,” Chem. Eng. Technol., 28: pp. 318–323.doi:10.1002/ceat.200407128 (2005).

5. Henke, L. and Winterbauer, H., “A Modular Micro Reactor for Mixed Acid Nitration,” Chem. Eng. Technol., 28: pp. 749–752. doi:10.1002/ceat.200500096 (2005).

6.  Pure Appl. Chem., Vol. 74, No. 12, pp. 2271-2276 (2002).http://dx.doi.org/10.1351/pac200274122271

KEYWORDS: microreactor, microreactor technology, microreactor(s), monopropellant, monopropellant ingredient(s), continuous processing, ionic liquid(s), energetic compound(s), advanced flow reactor(s), microchannel device(s), microstructures

AF171-062 TITLE: Sensor Open System Architecture (SOSA) Architectural Research

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Seek technology development of standards and architectures that provide uniformity, interoperability and open architecture while driving down procurement and operational costs for acquired weapon systems.

DESCRIPTION: The Sensor Open System Architecture (SOSA) is a C4ISR-focused technical and economic collaborative effort between the Air Force, Navy, Army, the Department of Defense (DoD), Industry, and other Governmental agencies to develop (and incorporate) technical Open Systems Architecture standards in order to maximize C4ISR sub-system, system, and platform affordability, re-configurability, overall performance, and hardware/software/firmware re-use. The SOSA effort will effectively create an operational and technical framework for the integration of disparate payloads into C4ISR systems; with a focus on the development of a functional decomposition for common multi-purpose backbone architecture for RADAR, EO/IR, SIGINT, EW, and Communications modalities. SOSA addresses hardware, software, and mechanical/electrical interfaces. The functional decomposition will produce a set of re-useable components, interfaces, and sub-systems that engender re-usable capabilities. This, in effect, creates a realistic and affordable ecosystem enabling mission effectiveness through systematic re-use of all available re-composed hardware, software, and electrical/mechanical base

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components and interfaces.

SOSA is an acquisition and technical environment for sensors and traditional C4ISR payloads which fosters innovation, industry engagement, and competition, and allows for rapid fielding of capabilities and platform mission reconfiguration, while minimizing logistical requirements with the following goals:

* Open creation of a Vendor, Platform agnostic, open and common architectural framework * Standardization of functional decomposition of Software, Hardware, Electrical/Mechanical interfaces * Harmonization with existing and emerging standards such as: FACE, OMS, SPIES, VICTORY, and VITA * Quality Attributes Maximize the applicability of SOSA-unique and JCIDS Quality Attributes * Cost-effective C4ISR systems which can rapidly respond to changing requirements and user needs

To that end this topic will concentrate on leveraging a series of draft SOSA technical standards to develop, implement, and prototype a scalable architecture solution that can support multiple phenomenologies such as: RADAR, SIGINT/EW, EO/IR, Communications, and EGI. The goal is to develop multi-use common capabilities solution that demonstrates reuse of similar functional components across two or more phenomenologies such as RADAR and SIGINT, or SIGINT/EW and EO/IR, while reducing physical/functional/electrical footprint in a POD or Turret enclosure.

All proposed solutions will be based on COTS components with SOSA standard interfaces that can demonstrate additional interoperability with two or more similar components from two or more commercial vendors with SOSA technologies. The interoperability will be demonstrated for common functional software capabilities, common physical (e.g., OpenVPX) cards interchangeability, and common electrical mechanical interfaces between a series of modules that may have different functionality sets based upon a series of needs (or requirements) for an application.

The results of the effort will be fully documented and presented to all relevant SOSA working groups as recommendations for potential changes to the standards; or proposals for future enhancements based on all lessons learned during implementation of the standards as part of any development program. This becomes part of an iterative process where the SOSA technical standards will improve as a result of consistent technical exchange between vendors and users

PHASE I: Research and develop an innovative reference architecture based on draft SOSA reference architecture standards for software, hardware, and electrical/mechanical interfaces. The reference architecture will flow from a series of general identified needs based upon applications. Identify gaps in the SOSA reference architecture and propose findings to the working groups for incorporation for the revision.

PHASE II: Instantiate the Phase I SOSA implementation solution for multiple sensing modalities and identify multi-service deployment opportunities including unmanned air vehicle (UAS) /POD/ Turret/ Truck/ Humvee/ Ship/ Plane for USAF, Army, and Navy systems. Identify commonality of reuse within modalities, between DoD services, and deployment form factors. Any designed and produced prototype will have focus on cross modality and cross functionality.

PHASE III DUAL USE APPLICATIONS: Deploy SOSA prototype solution in a functional test environment to validate solution. Document lessons learned (what worked, what did not, areas of improvement). Identify gaps in SOSA reference architecture standards and propose a solution to the identified gap back to the SOSA working groups.

REFERENCES:1. Frank Kendall, "Memorandum for Secretaries of the Military Departments Deputy Chief Management Officer Department of Defense Chief Information Officer Directors of the Defense Agencies AT&L Direct Reports, Subject: Implementation Directive for Better Buying Power 3.0 - Achieving Dominant Capabilities through Technical Excellence and Innovation," April 9 2015.

2. Young, John J. Jr. "Memorandum for Deputy Under Secretary of Defense for Acquisition and Technology, Director, Defense Research and Engineering, Subject: Radar Open System Architecture Defense Support Team

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(DST)," 19 February 2009.

3. Lucero, Scott and Scott Kordella,"Radar Open Architecture Defense Support Team Industry Day," April 8-9, 2010, Solicitation Number LLR0304101452, 4 March 2010. Mr. Scott Lucero, et al "DoD's Perspective on Radar Open Architectures" MITRE, June 2010

4. VITA 65 (OpenVPX) Standard, v3.00, September, 2013.

KEYWORDS: Standards, Open Architecture, Sensors, Multi-INT, RADAR, SIGINT, Electronic Warfare (EW), Communications, Electro optical (EO), Infrared EO/IR, Hardware, Software, Electrical, Mechanical, Interfaces

AF171-063 TITLE: Electronically Controlled Adaptive Polarization for Compact Broadband Transmitters and Receivers

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Identify advanced concepts for adaptive polarization for use in compact, high-reliability broadband transmit and receive antenna system applications

DESCRIPTION: Adaptive polarization embues flexibilities in radio-frequency systems by adding degrees of freedom in the antenna that can increase performance in aerospace platforms. A simple approach to incorporating an adaptive polarization capability into any single transmitter or receiver involves integrating multiple antennas with differing polarizations together to form a switchable multi-element antenna matrix. Using a multi-throw RF switch, each antenna input or output can be selected as required. This approach has even been integrated into a common aperture, one such design is known as the sinuous antenna[1], but for a single transmitter or receiver, it would require external RF switching and control to isolate a particular antenna element polarization for use on the onboard platform. This approach is also traditionally limited to low-gain and low-power applications.

Incorporating multiple antenna elements of differing polarizations to accomplish adaptive polarization is challenging when compact physical size and reliability is a concern. Traditional solutions such as the largely electromechanical designs (e.g., involving a servo mechanism to physically rotate a polarizer assembly in order to achieve adaptive polarization ability) are not likely practical in these cases, hence the present interest in more creative technology approaches. It is expected that a more optimal solution would examine solid state alternatives to present electromechanical design, leading to a faster, and higher reliability, non-mechanical approach.

The goal of this topic is to research and develop the technology to create compact and lightweight polarizer assemblies for use in both high and low power transmit and receive antennas that will accomplish adaptive polarization by purely electronic means for high reliability and fast response time. Air Force is interested in addressing primary relevant communications bands (UHF,S,L,X, and Ka) predominately, and understanding the challenges in extending to other parts of the electromagnetic spectrum.

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We encourage creative technology approaches to the adaptive polarization problem, to include concepts for extremely reconfigurable antennas. Offerors should consider the practical issues of signal distribution and the management of control planes for the effective management of polarization "on the fly". Agility is preferred to the degree practical, along with compactness, reliability, ease of integration. For spaceborne applications, it is important to address the constraints imposed by the space environment in terms of radiation, power consumption, thermal management, and other factors. Offerors should provide compelling evidence of a traceable path to a qualified and affordable implementation of any ideas proposed.

PHASE I: Research and develop novel polarizer technologies involving no moving parts (for example the meander-line polarizers described in Reference [2] and similar impactful approaches). For example, the Reference [2] concept as applied to this SBIR, might be duplicate layers of meander-line planes that are orthogonal to each other, and activated by electronic means such as solid state relays or PIN diodes actively connecting each segment over multiple circuit board layers, in order to control the direction of circular polarization. Perform simulation modeling of the proposed concept and provide a credible path to demonstratable formulation.

PHASE II: Develop and test prototype polarizer assemblies using a test setup in a small anechoic chamber to demonstrate intended function of the design.

PHASE III DUAL USE APPLICATIONS: Develop, environmentally qualify, integrate, and test production-representative, application-specific polarizer assemblies and associated electronic control circuitry in military airborne antenna systems in a large anechoic chamber.

REFERENCES:1. Antenna Engineering Handbook (III Ed.), Chapter 14, Frequency Independent Antennas, R. H. Du Hamel and J. P. Scherer, edited by Richard C. Johnson, McGraw-Hill Publishers, 1993.

2. Antennas and Propagation, IEEE Transactions on Antennas and Propagation includes theoretical and experimental advances in antennas (Volume: 21, Issue: 3), May 1973.

KEYWORDS: Adaptive, Polarization, Antenna, Polarizer, Compact, High-Reliability

AF171-064 TITLE: Energy Storage System

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Development and demonstration of a rechargeable energy storage system that is able to provide storage to lift 14000lbs 120” within 15 seconds and 40” in 7 seconds where the motion will stop.

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DESCRIPTION: The U.S. Air force has several energy storage solutions which fall sort of the required 14000lbs 120” within 15 seconds and 40” in 7 seconds. The new energy storage system will have to comply with MIL-STD 461G Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment and MIL STD- 810G Environmental Engineering Considerations and Laboratory Tests.

A new more reliable energy storage system is desired to maintain decreased security manpower requirements through the use of a denial system. The new system should be readily transferable into the current systems' place without major redesign of any other components or facilities. The new energy system will be recharged using 120V 60 Hz commercial power.

The movement characterization is a 14000lbs. concrete plug moving faster for 15 seconds for 120: then slowing down to a complete stop in 40” over 7 seconds using a 100 Hp, 460 VAC (nominal max), 60 Hz, 130 – 160 amp induction motor and telescoping ball screw. These are the allotted times required to fully secure the plug within the required amount of time.

PHASE I: Establish feasibility and technical merit of proposed solution through modeling and design analysis focused on the capability to lift 14000 lbs. 180 in 3 times via a telescoping screw. Component level tests of the required loads should be performed to validate the modeling and design analysis.

PHASE II: Manufacture and test a prototype enclosure/test article defined by the US Air Force sponsor to verify manufacturability and performance of energy storage system through use of developed testing method or with coordination through AFNWC/NI offices use of Strategic Missile Integration Center. Prototype will demonstrate lifting capability 3 times with minimal delay between each lift. The prototype will also show recharge through use of commercial power (120V 60 Hz).

PHASE III DUAL USE APPLICATIONS: Commercial Application: Applications could include load leveling for electric utilities, or regenerative braking energy storage for automotive use. Military Application: Reliable energy source to provide enhanced security to government assets reducing the required security forces manpower.

REFERENCES:1. MIL-STD-461G Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment.

2. MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests.

KEYWORDS: Energy, Storage, Security, ICBM, Electric, Electricity

AF171-065 TITLE: Effects of GPS Degraded or Denied Environments on Delivery Vehicles

TECHNOLOGY AREA(S): Nuclear Technology

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon,

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gail.nyikon@us.af.mil.

OBJECTIVE: Perform Nuclear Command, Control & Communications (NC3) position, navigation, and timing (PNT) effects analysis of a degraded positioning system on Command and Control functions. The main focus is to understand potential effects on the delivery vehicle in a GPS degraded or denied environment and provide novel solutions to operate through these conditions.

DESCRIPTION: The US Air Force needs a reliable capability with integrated redundancy to maintain capabilities and Situational Awareness (SA) with respect to position, navigation, control, and timing of a delivery vehicle in a GPS denied or degraded environment. Though military GPS signals (e.g. P(Y) and M-code) are less susceptible to attack via spoofing and are used with technologies that are more jam-resistant, background signals can still produce high enough jammer-to-signal ratios to affect receiver PNT accuracy. Robust solutions are needed to ensure effective operations of delivery platforms including but not limited to airborne, and reentry platforms. Currently, the Air Force has very few alternatives to accomplish mission objectives when GPS is denied or removed from the equation leading to loss of position and target information and possibly denying the accomplishment of mission objectives. This SBIR topic seeks solutions in the form of modeling and simulation, hardware, architectural redundancy studies and/or concepts of operations which will enable successful mission operations in GPS denied or degraded environments. Alternative methods of navigation should be compatible with the size, weight, and power (SWaP) requirements of airborne and reentry platforms. Technologies approaching GPS PNT accuracy may be considered from a range of options including Ground-Based Augmentation Systems (GBAS), Ground-Based PNT Systems (GBPS), and Hybrid and Alternative PNT Systems (HAPS). Additional requirements to consider relate to availability and performance while operating in a GPS denied/degraded environment, resistance to jamming, all-weather operations, and operating in a radio-frequency (RF) challenged environment.

PHASE I: Research and identify models that accurately simulate delivery vehicle behavior in GPS denied or degraded environments utilizing advanced technology. Develop feasibility study and deliver design specs for possible robust solutions.

PHASE II: Demonstrate effects and draw conclusions through simulation results of GPS denied or degraded environments to define possible way forward to mitigate Position, Navigation, and Timing (PNT) errors. Perform tests to validate models and simulations created in Phase I. Build prototype as proof of concept through modeling and simulation or hardware realization to deliver to government to be tested in a GPS denied or degraded environment.

PHASE III DUAL USE APPLICATIONS: Test fidelity of prototype for functionality and manufacturability. Commercial applications allow for location based systems to continue to reliably operate in denied or degraded environments from simple port navigation to search and rescue applications when GPS signals are compromised. Military applications include the ability to locate and direct military assets in denied, or degraded environments.

REFERENCES:1. Polle, B., "Performance Analysis and Flight Data Results of Innovative Vision-based Navigation in GPS-denied Environment," Proceedings of the 25th International Technical Meeting of The Satellite Division of the Institute of Navigation (ION GNSS 2012), Nashville, TN, September 2012, pp. 2104-2115.

2. Stubbs, Joshua, Akos, Dennis, "GNSS/GPS Robustness for UAS," Proceedings of the 2016 International Technical Meeting of The Institute of Navigation, Monterey, California, January 2016, pp. 485-493.

3. Hardy, Jeremy, Strader, Jared, Gross, Jason N., Gu, Yu, Keck, Mark, Douglas, Joel, Taylor, Clark, "Unmanned Aerial Vehicle Relative Navigation in GPS Denied Environments," Proceedings of IEEE/ION PLANS 2016, Savannah, GA, April 2016, pp. 344-352.

4. “Nuclear Command, Control, and Communications”, Curtis E. Lemay Center for Doctrine Development and Education,https://doctrine.af.mil/download.jsp?filename=3-72-D30-NUKE-OPS-NC3.pdf

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5. Atia, M. M., Noureldin, A., Georgy, J., Korenberg, M., "Bayesian Filtering Based WiFi/INS Integrated Navigation Solution for GPS-Denied Environments", NAVIGATION, Journal of The Institute of Navigation, Vol. 58, No. 2, Summer 2011, pp. 111-125.

KEYWORDS: GPS, denied, degraded, position, navigation, command, control

AF171-066 TITLE: Real-Time Threat Database

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a threat scenario database architecture for space situational awareness and defensive space control which will enhance the ability to detect and characterize anomalous conditions in a timely fashion.

DESCRIPTION: In today's environment space system threat and anomaly detection, assessment, and response is currently very ad-hoc for a number of reasons. Most threats and anomalies manifest themselves in a non-deterministic fashion and because of that detection and resolution methodologies are often treated as one off situations. Today’s space system operations currently have limited ability to correlate current events with historical events in an automated fashion. What is needed is a more robust, flexible system that would allow the processing of fuzzy information and which would enable correlating current scenarios with past scenarios while accounting for differences in the scenarios. Benefits of a system like that would include reduced response time to events, reduced operations manpower, and improved overall situational awareness and command and control of our space systems. In addition to the complexity inherent within the non-deterministic nature of the anomalies, the problem is made more challenging because relevant information sources may be on heterogeneous and dislocated systems. Another flaw in current systems is the difficulty in building and validating reasoning systems used for space superiority. The focus of this topic is to seek out innovative ideas for how to accomplish this challenging problem. Proposals are sought which would enable capturing historical scenarios and then correlating new and evolving scenarios with historical occurrences. As an example case-based reasoning technology provides a possible technology avenue to accomplish this objective. A case-based like reasoning system could provide a natural way to capture events in real-time, providing real-time validation, and then to extend the system over time as new events occur. Other technologies might include fuzzy logic, expert systems, or neural networks or some combination of the above. Successful proposals would include a good technical design of the decision support system in question as well as demonstrate a solid understanding of the space system environment. Proposals should consider the types of data sources that would be relevant as well as to address how information across disparate systems would be aggregated. Consideration should be given as to how the proposed system would function within existing space system command and control environments. System flexibility should also be a key, as ideally the system would provide the ability to dynamically update its database.

PHASE I: Phase 1 of this topic would result in a solid system design with consideration to information sources, reasoning logic used, update methodology, and traceability to relevant space systems. A limited proof of concept demo in the JSpOC and/or JICSPOC and within the Joint Space Operations Center (JSpOC) Mission System (JMS)

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architecture.

PHASE II: Phase 2 of this topic would include a fuller implementation of the design developed in phase 1 and include relevant data sources. Implementation and demonstration within the JMS infrastructure would be highly desirable. Phase 2 should also include a proposed plan for how the limited system could integrate within our existing Air Force command and control infrastructure.

PHASE III DUAL USE APPLICATIONS: The proposed system has potential applicability to both single satellite operations as well as combined satellite operations environments. A likely transition path is through the JMS program via the ARCADE testbed.

REFERENCES:1. R Haga, J Saleh, "Epidemiology of satellite anomalies and failures: A subsystem-centric approach ", Publication of Acta Astronautica, Vol 69, Issues 7-8, Oct 2011.

2. J Kolodner, "Case Based Reasoning", Morgan Kaufmann Publishers, 1993.

3. M Nogueria, M Balduccini, M Gelfond, Ra Watson, M Barry, "An A-Prolog decision support system for the space shuttle",http://www.researchgate.net/publication/2326923_An_A-Prolog_decision_support_system_for_the_Space_Shuttle.

KEYWORDS: Anomaly detection, space situational awareness, threat detection, space superiority, satellite course of action

AF171-067 TITLE: Miniaturization of Comprehensive Energetic Charged Particle Detectors for Anomaly Attribution

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Drive Size, Weight, and Power lower by a factor of 2x to 4x for Energetic Charged Particle sensors over current designs.

DESCRIPTION: With new policy requiring Energetic Charged Particle (ECP) sensors on all new Air Force satellite acquisitions, it is incumbent to miniaturize the system to allow implementation across the fleet as the Air Force moves toward smaller and disaggregated constellations. While current designs (4kg, 10W, 3600cc) are acceptable for large space systems, many missions will be accomplished in the small satellite class (100kg). For systems this small, either the ECP policy will need to be waived, leaving a gap in attribution capability, or a miniaturized sensor with SWaP reduction by a factor of 2x to 4x needs to be developed while still meeting ECP requirements.

Space environment impacts are rare, and typically only happen during times of extreme particle flux.[1] However, a

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space environment sensor also needs to conclusively measure a normal environment to rule out environmental impacts. This means an ECP sensor for anomaly resolution will be required to differentiate between various extreme environments while still also measuring the normal environment. This has created extreme requirements in terms of flux and energy range. Additionally, the environment must be measured with sufficient resolution to differentiate a hazardous from a non-hazardous environment.

The net requirement is to measure electrons from 100eV to 5MeV and protons from 2MeV to 100MeV from median to the 99th percentile climatology (roughly four orders of magnitude at a given energy channel). Energy channel spacing must be better than a factor of 1.8 across the sensor range, and the detectors must be able to determine the omnidirectional flux as well as estimate the peak directional flux (if within the field of view) within a factor of 4 accounting for all error sources and within a factor 2 for the combination of systematic error with uncertainties resulting from field of view limitations, including background fluxes and cross-contamination. The design must not saturate within the required flux ranges and the response shall not roll over for fluxes exceeding these ranges. Current designs deal with this by dividing the energy range between multiple sensors so the flux range each sensor has to deal with are manageable. [e.g. 2,3] Additionally, the instruments must be rated to survive in space for the mission life of the host vehicle, often up to 15 years.

The initial goal is to identify candidate technologies and innovative concepts that would allow a reduction in SWaP, for example by increasing the energy and flux range of single sensors, enhancing the speed at which the detectors and associated electronics can count particles, or reducing the size of the detector.

The final goal is to develop and qualify for spaceflight technologies enabling a reduction in ECP SWaP by a factor of 2x to 4x.

PHASE I: Review sensor technologies and provide estimates of how to best accomplish reductions in SWaP for ECP sensors. Review candidate technologies and provide a recommended technical approach for Phase II.

PHASE II: Develop prototype sensors and perform high-fidelity modeling of performance, verifying response under laboratory and calibration facility test.

PHASE III DUAL USE APPLICATIONS: Refine concept and develop space-qualified detector(s) capable of integration into future ECP systems or direct integration on AF satellites by SMC prime contractors. It is expected that there will be commercial interest in sensor technologies as well.

REFERENCES:1. O’Brien, T. P. (2009), SEAES-GEO: A spacecraft environmental anomalies expert system for geo-synchronous orbit, Space Weather, 7, S09003, doi:10.1029/2009SW000473.

2. Dichter, B. K. et. al, Compact Environmental Anomaly Sensor (CEASE): A Novel Spacecraft Instrument for In Situ Measurement of Environmental Conditions, IEEE Trans. On Nucl. Sci., 45(6), 2758-2764, 1998.

3. Lindstrom, C.D. et. al, Characterization of Teledyne microdosimeters for space weather applications, Proc. SPIE 8148, Solar Physics and Space Weather Instrumentation IV, 814806 (September 29, 2011); doi:10.1117/12.893814

4. White Paper on ECP Energy Range and Flux Requirements

KEYWORDS: spacecraft, anomaly, attribution, energetic charged particle, ECP

AF171-068 TITLE: Non Destructive Trusted FPGA Verification

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TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop new methodologies to assess and verify Field Programmable Gate Array (FPGA) trust and integrity.

DESCRIPTION: FPGAs provide complex processing tailored to individual applications without requiring expensive custom integrated circuit (IC) development. With the highest density circuit fabrication facilities now overseas, high performance (smaller size; less weight and power) devices cannot be acquired through trusted sources. This SBIR solicits research and development that would lead to raising the levels of trust of high performance FPGA technologies.

The goal is to produce hardware and/or software components to validate FPGA integrity. Significant payoff will result with national space programs, missile programs, and ground hardware programs being able to use state of the art FPGAs (that have more capability with lower size, weight and power) that may not be manufactured in a fully trusted foundry. The goal is to develop new methodologies to assess FPGA hardware and/or software validate trust and integrity. Near term targeted programs are Spaced Based Infrared System (SBIRS) High, Overhead Persistent Infrared (OPIR), a Space Situational Awareness follow-on system, and others. If other IC devices are considered, then nearly all DOD programs would benefit.

PHASE I: Phase 1, Develop innovative non-destructive approach and strategy to verifying FPGA chip integrity. Hardware based, software based, or a combination is acceptable. The Phase I effort should justify the proposed hardware-based, software-based, or combined approach proposed.

PHASE II: Phase 2, Develop the concepts of the Phase I research for implementation in Phase II to include definition of technology and preliminary designs (TRL 3) to validate and prove concepts.

PHASE III DUAL USE APPLICATIONS: In this phase, mature the technology and develop into a product for commercialization. This technology has potential applications across the commercial market as it provides a means to validate microchip integrity thereby lowing the risk of use for microelectronics manufactured in oversees foundries. As such, all commercial markets that utilize microelectronics could benefit from this validation technology.One approach for commercialization follows:Step 1, Prototype (TRL 4/5) demonstration to show feasibility on actual and test FPGAs.Step 2, Methods fully verified (TLR 6) with a variety of devices.Step 3, Integrate methodology into the overall supply chain.

REFERENCES:1. Mike Johnson & Brandon Eams, On the Assessment of Trust in Development Tools, Intellectual Property and Applications Targeting FPGAs, Microelectronics @ NSA Symposium, 10-12 Mar 2015.

2. Stephen Trimberger & Jason Moore, Xilinx, FPGA Security: Motivations, Features, and Applications, Proceedings of the IEEE, Vol. 102, No. 8, Aug 2014.

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KEYWORDS: trusted, FPGA

AF171-069 TITLE: Improved Data Fusion Techniques for Space-Based Remote Sensing

TECHNOLOGY AREA(S): Space Platforms

OBJECTIVE: Develop and implement alternative/innovative fusion techniques to include traditional and non-traditional data sources for improvement in performance, and/or cost reductions for Remote Sensing missions.

DESCRIPTION: Develop innovative technology improvements for concepts, methods, techniques or approaches for data fusion algorithms using Overhead Persistent Infra-Red (OPIR) source[s] and potentially alternate sensors that provide significant improvement in performance, and/or reduces cost for Remote Sensing missions, including OPIR, civil monitoring and Weather. This may include, but is not limited to: improvements in the speed, performance and/or accuracy of traditional fusion algorithms; fusion of non-traditional sources with OPIR; and/or alternative fusion methods that result in enhanced performance. Transition of capabilities include evaluation/validation at the Government TAP Room Laboratory in Boulder, CO then the SBIRS OBAC for operational assessment.

The goal is to demonstrate and evaluate the developed fusion concept in an operational-like environment. Once the TAP Room Laboratory is open, an environment for developers will exist for developers to investigate unique, innovative fusion techniques, traditional and non-traditional fusion source combinations. SBIRS Data will be available in the TAP Room initially, however plans for VIIRS and DMSP data are in the works. Additional data sources as needed/specified by developers may be necessary in the future. Alternative sources of data may serve to validate/increase confidence, accuracy of otherwise single source data, and/or increase spectral, spatial and/or temporal resolution. Application to multiple mission areas through fusion of alternate sources will increase utility of data and provide cost savings to the Government. Specific mission application to Missile Warning, Missile Defense, and Battlespace Awareness are desired, i.e. application of alternate remote sensing data to support those missions in terms of clutter rejection, atmospheric phenomena, for detection, typing/discrimination and tactical parameter estimation performance.

The products of this effort will be installed, integrated and tested at the RS TAP Room laboratory in Boulder, Colorado, where SBIRS, potentially other OPIR and eventually weather data will be available. The product will be evaluated alongside and against other fusion and exploitation products. Operational users will be on hand to evaluate the utility and performance of the products. Products that provide value and support the RS Mission will be transitioned to the OBAC and/or other operational sites as determined once sufficient testing has taken place.

PHASE I: Identify and develop an initial concept, design approach and prototype for an innovative fusion concept, technique or combination of traditional and non-traditional sources. Testing is encouraged. Experimentation with recorded and/or simulated data is encouraged.

PHASE II: Refine and implement design from Phase 1. Conduct comprehensive testing and analysis with focus on testing and evaluation using live data sources. Testing in an operational-like environment with live data is required.Demonstrate and evaluate the developed fusion concept in an operational-like environment with end users.

PHASE III DUAL USE APPLICATIONS: Successfully demonstrated and validated data fusion techniques that provide value to the RS Mission will be transitioned to the OBAC and/or other operational sites as determined once sufficient testing has taken place.

REFERENCES:1. Mark Bedworth, Jane O'Brien, James Llinas, Research Gate Article, Data Fusion: The Benefits of Collaboration and Barriers to the Process, Jan 07, 2015.

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2. James L. Crowley, Yves Demazeau, Signal Processing Article, Principles and Techniques for Sensor Data Fusion, 1993.

3. Y.A. Vershinin, IEEE: Information Fusion, a Data Fusion Algorithm for Multi-Sensor Systems, 2002.

4. M. Kastek; R. Dulski; M. Zyczkowski; M. Szustakowski; W. Ciurapinski; K. Firmanty; N Palka; G. Bieszczad, SPIE Proceedings, Multisensor Systems for Security of critical infrastructures: concept, data fusion and experimental results, September 8, 2011.

KEYWORDS: Data Fusion, Event Detection, Typing/Discrimination. Tactical Parameter Estimation, Multi-source fusion, SBIRS, OPIR

AF171-070 TITLE: Advanced Solar Cell Metallization

TECHNOLOGY AREA(S): Space Platforms

OBJECTIVE: Develop innovative concepts for producing solar cell metallization which will provide performance resilience to the presence of semiconductor cracks.

DESCRIPTION: Presently, crystalline solar cells (e.g. silicon, gallium arsenide, etc.) can degrade from cleaving or fracturing along crystallographic planes under mechanical stress. This degradation mechanism is being exacerbated due to the trend for the use ever thinner solar cell structures as a means of saving mass, reducing materials costs and improving device performance. Generally speaking, solar cells with cracks or cleaves do not suffer performance degradation unless the fracture extends through the metallization on the front and/or rear surface of the device [4]. Should the metallization also fracture, as is extremely common, the solar cell performance can suffer due to increased series resistance or even loss of active solar cell area.

Recent research has demonstrated that metal matrix composite (MMC) solar cell metallization has the potential to provide electrical connectivity across large (> 30 micron) fractures [1-3]. These MMC materials, consisting of multi-wall carbon nanotubes in silver, have demonstrated the ability to “self-heal” should they be strained to electrical failure. A wide variety of approaches for depositing MMC metallization have been explored, including electroplating, spray coating, film transfer and screen printing.

The goal of this research effort is the development of an advanced solar cell metallization that has the ability to maintain solar cell performance in the presence of cleaves or fractures in the semiconductor material. The material may accomplish this function by being immune to fracture or by providing good electrical conductivity across fractures. A successful technology should demonstrate a < 5% performance degradation in the solar cell should a fracture occur. The materials and deposition processes should be suitable for high-volume, low-cost deposition as there is potential application of this technology for both space and terrestrial solar cell technologies.

The solar cell metallization technology should be capable of supporting a 15-year mission in GEO or Medium Earth Orbit (MEO) and 5 years in Low Earth Orbit (LEO) after ground storage of 5 years.

PHASE I: Perform preliminary analysis and conduct trade studies to validate concepts for the advanced metallization. Perform preliminary risk mitigation experiments to validate metallization components and deposition approaches. Demonstrate preliminary crack-tolerance behavior.

PHASE II: Fabricate and deliver engineering demonstration units consisting of advanced metallization integrated with operational solar cells (e.g. space triple junction solar cells, terrestrial silicon solar cells, etc). Demonstrate ability of metallization technology to provide fracture/crack tolerance for device performance and ability to be

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integrated into appropriate higher order assemblies (e.g. panels, modules) with high reliability interconnects, etc.

PHASE III DUAL USE APPLICATIONS: Transition the solar cell metallization technology developed for use on DoD, NASA or Commercial spacecraft.

REFERENCES:1. Silver–Carbon-Nanotube Metal Matrix Composites for Metal Contacts on Space Photovoltaic Cells, Omar K. Abudayyeh; Nathan D. Gapp; Cayla Nelson; David M. Wilt; Sang M. Han, IEEE Journal of Photovoltaics, Year: 2016, Volume: 6, Issue: 1 Pages: 337 – 342.

2. Carbon nanotube metal matrix composites for solar cell electrodes, Nathanael D. Cox; Jamie E. Rossi; Brian J. Landi, Photovoltaic Specialist Conference (PVSC), 2015 IEEE 42nd, Year: 2015.

3. Carbon nanotube reinforced cu metal matrix composites for current collection from space photovoltaics, Adam B. Phillips; Brandon L. Tompkins; Zhaoning Song; Rajendra R. Khanal; Geethika K. Liyanage; Nathan D. Gapp; David M. Wilt; Michael J. Heben, Phot

4. Quantitative local current-voltage analysis with different spatially-resolved camera based techniques of silicon solar cells with cracks, Tobias M. Pletzer; Justus I. van Mölken; Sven Rißland; Brett Hallam; Emanuele Cornagliotti; Joachim John; Otwin Br

KEYWORDS: Solar Cell, Metallization, Resilience, Crack-tolerant

AF171-071 TITLE: Integration of Tactical and Individual Satellite Operations with Global Operation and Control

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop, integrate, and demonstrate a toolset which would enable seamless integrate of individual and tactical satellite operations centers with a higher level operations center Space Operations Center such as the JSpOC.

DESCRIPTION: The Joint Space Operations Center (JSpOC) has the function of maintaining near real-time situational awareness of all space assets. Unfortunately, today’s Air Force satellites are largely operated from a heterogeneous set of operations centers on isolated networks. Satellite data, both relating to system state of health and that relating to payload ("mission products"), flows from these centers in general using laborious manual processes with limited automation. This construct results in delays in reporting, delays in responding to anomalous conditions, and hinders the ability to obtain real time situational awareness for our space assets.

As a method to integrate these individual operations centers, the Air Force is exploring strategies that greatly

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enhance automation, such as the use of approaches like GMSEC (Reference 1) as an infrastructure for the management of satellite operations data. If successful, this will enable standardization of satellite operations for ground assets through service-oriented architectures. Approaches such as GMSEC have been shown to dramatically reduce complexity, by providing unified mechanisms to expose and manage both control and data products associated with these systems. This can lead to a significant reduction of the operational footprint (through improved prospects for automation), as well as increased timeliness in the gathering and analysis of data. The unification promotes development of tools and decision aids, contributing to a more uniform situational awareness of systems associated with this improved infrastructure.

Meanwhile, the JSpOC Mission System (JMS) has been developing a net-centric infrastructure to promote/enable real-time space system awareness using a large number of net-centric command and control and space situational awareness tools. The problem is that to date JMS and GMSEC have been developed independently, with little thought as to their effective integration. Integration of the two systems would allow the real-time flow of satellite events to the JSpOC.

Additionally, we would like to further expanding the utility of these approaches. For example, for Operationally Responsive Space (ORS), warfighters expect to ability to directly task space assets in near real time disseminating of mission products from the assets to the theater. While the theoretic possibility of such concepts has been shown in limited demonstrations, the ability to task assets should have the capability to access all necessaryinformation while eliminating inefficiencies that would not scale especially if the demonstrated warfighter tasking systems were to be used operationally.

JMS data services can be developed which would enable utilizing near real-time awareness of areas such as terrestrial and space weather, orbital position, and target information. Use of this information in a warfighter tasking system would enable optimization of satellite tasking and avoid loss of data.

The objective of this topic is to develop an effective bridge between GMSEC and JMS and to demonstrate this capability via a set of operational use cases. One approach, for example, might involve a set of modules to allow the seamless transfer of data between GMSEC and JMS. It is envisioned that success proposers will work closely with the Air Force in order to leverage existing technologies and to ensure technical efforts are consistent with overall responsive satellite development goals. Proposed concepts should strive for designs that can eventually lead to development of a complete comprehensive system, i.e., scalable to operational settings.

PHASE I: Design, develop, and demonstrate a robust set of software modules that would enable seamless transfer of satellite system information between JMS and GMSEC. A proof of concept demonstration with a representative set of use cases is highly desirable. Utilize test results to identify key technical challenges, develop a mitigation strategy, and to develop the Phase II program plan.

PHASE II: Utilizing the results of phase 1, develop and demonstrate a more robust system using an approved set of space system scenarios in a relevant environment. The demonstration should achieve the functional and interface specifications of the SMC/AD Enterprise Ground Systems (EGS).

PHASE III DUAL USE APPLICATIONS: The proposed effort would develop satellite system technologies that are applicable to both commercial and military satellites. In particular the technologies would have applicability to NASA which also operates a large number of space assets.

REFERENCES:1. GMSEC home page, NASA/GSFC,http://gmsec.gsfc.nasa.gov/.

2. Rico Espindola and Gayla Walden, Aerospace Corp, “Developing a Responsive Ground System Enterprise”, Aerospace Corp Magazine Summer 2009 Edition.

3. DISA Net Centric Enterprise Services,http://www.disa.mil/nces/.

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KEYWORDS: GMSEC, JSpoC Mission Systems, JMS, Net Centric Space systems, Satellite Operations, Satellite Tactical operations, responsive space

AF171-072 TITLE: Integrated Photon Management for Multijunction Solar Cells

TECHNOLOGY AREA(S): Space Platforms

OBJECTIVE: Technologies are sought to improve the radiation hardness of multijunction solar cells while improving their conversion efficiency through the use of integrated photon management features.

DESCRIPTION: III-V multijunction solar cells are the highest efficiency and most widely used solar cell technology currently used on spacecraft. Many aspects go into the design of space solar cells, including means for mitigating degradation due to high energy proton and electron radiation. Current generation space solar cells are comprised of a GaInP top subcell, a GaAs middle subcell, and a Ge bottom subcell. In this material configuration, the GaAs middle subcell is generally the most susceptible to damage from radiation. At end-of-life, the solar cell is usually limited in current by this GaAs subcell. In addition, as trends continue towards higher number of subcells (4+) in a space solar cell, the vulnerability to radiation degradation increases.

This solicitation is looking for methods by which the radiation hardness and performance of a multijunction solar cell can be improved using integrated photon management techniques such that full optical absorption may be accomplished with a significantly thinner absorber region. The direct result should be an increase in remaining factor (final power / initial power), relative to current state-of-the-art. These techniques may include photon scattering/trapping or plasmonic structures that are built into the device structure itself. Due to the light scattering or coupling, the thickness of a given subcell could be decreased without adversely impacting the current through the cell. In turn, the degradation to minority carrier diffusion lengths due to radiation damage will have a lesser impact on end-of-life performance. Additionally, the reduced thickness provides a potential benefit to the subcell voltage due to a lower saturation current.

Initial development of integrated photon management structures should target the weakest subcell within a multijunction solar cell. For the current generation cell mentioned above, this would mean targeting the GaAs subcell. However, other multijunction solar cells, such as the inverted metamorphic multijunction (IMM), upright metamorphic multijunction (UMM), or other high-efficiency cells may be used as a baseline. The proposed designs for integrated photon management features should be tested within a multijunction structure. This solicitation is not interested in enhancements for single junction structures. The technologies proposed should be capable of successfully being qualified via standards such as AIAA S-111 for solar cells.

The solar cell technology should be capable of supporting a 15-year mission in GEO or Medium Earth Orbit (MEO) and 5 years in Low Earth Orbit (LEO) after ground storage of 5 years.

PHASE I: Phase I should examine test cases by which full optical absorption in a sub-cell of a multijunction stack can be realized in significantly thinner absorber layers using integrated photon management features. Analysis of the proposed methods should be performed and initial proof-of-concept testing should be demonstrated, with a potential down select.

PHASE II: Phase II builds upon the analysis and testing performed in Phase I to further refine the technologies of interest. Identified technologies should be evaluated for their radiation hardness and overall cell performance metrics. Demonstration of the technology should be performed, including electron radiation testing.

PHASE III DUAL USE APPLICATIONS: Phase III further matures the technology developed in Phase II and should result in a solar technology which is ready to enter qualification testing (e.g., AIAA S-111).

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REFERENCES:1. H. A. Atwater and A. Polman, Nat. Mater.,vol. 9, pp. 205-213, 2010.

2. V. K. Narasimhan and Y. Cui, Nanophotonics, vol. 2, no. 3, pp. 187-210, 2013.

3. R. B. Wehrspohn and J. Upping, J. Opt., vol. 14, no. 2, pp. 024003, 2012.

KEYWORDS: spacecraft, multijunction solar cell, photon management, radiation hardness

AF171-073 TITLE: Weather Satellite

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a mission concept and low earth orbit small satellite bus and/or small sensor payload suitable for timely global multispectral imaging of cloud cover for military operations. Consider other data sources for a heterogeneous architecture.

DESCRIPTION: The Department of Defense (DOD) uses data from military, U.S. civil government, and international partner satellite sensors to provide critical weather information and forecasts for military operations. The DOD’s primary existing weather satellite system is the Defense Meteorological Satellite Program (DMSP), which will soon be removed from operational service. The United States Strategic Command (USSTRATCOM) has identified potential future needs in the current weather infrastructure to support tactical operations: Cloud Characterization and Theater Weather Imagery. Timely multispectral satellite imagery addresses both needs. Required resolution is 1 km in visible and 2 km in IR. Required timeliness is revisits in 4 hours or less. Data formats are to be compatible with existing weather processing centers. Post processing should be rapid enough to ensure tactical availability of data within 10 minutes of ground readout. There may be flexibility in these spectral bands and other requirements by clarifying with tactical operators what specific mission utility is required. System trades will be performed to evaluate alternative mission concepts that could include newly deployed satellite(s) to LEO or GEO, hosted payloads, existing military or commercial satellite systems, or alternative data sources. Ground or airborne sensors may be considered but must be part of a solution for tactical operations in hostile denied areas. The most cost effective solution that meets the required performance described above will be selected as the baseline approach.

In addition to evaluating alternative mission concepts, a low-cost LEO satellite design will also be developed to a preliminary design review (PDR) level for the Phase I. This LEO satellite design could be one of several identical satellites in a dedicated LEO constellation or one element of a heterogeneous architecture leveraging data from other satellites or sources.

The Phase II will mature the LEO small satellite mission concept for timely global multispectral imaging of cloud cover, according to the requirements outlined above. The space segment design will include the satellite bus and

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payload, and interfaces / requirements for launch and operations, including ground communications links. The Phase II will further develop and deliver a space qualifiable LEO small satellite bus and/or sensor payload to perform multispectral imaging of cloud cover. The satellite bus should utilize standard or prescribed interfaces to proposed launch vehicles and ground segment. Commonly available industry standard data and mechanical interfaces should be used between the payload and bus, if opting to deliver only one or the other, e.g., standard fastener sizes, RS-422, Ethernet, etc. Details of these interfaces may be modified during the course of the effort to accommodate other awardees.

PHASE I: Develop a low-cost mission concept to provide cloud cover and characterization data and design a LEO satellite.1. Conduct trades to identify mission concept(s) to provide timely global multispectral imaging of cloud cover at minimal system cost.2. PDR Design of LEO satellite to provide 1 km resolution, multi-spectral imagery of cloud cover, including sensor, orbital configuration, and downlinks.

PHASE II: Based on the Phase I effort, develop and deliver a space qualifiable LEO small satellite bus and/or sensor payload to provide cloud cover and characterization data.1. Utilize standard interfaces to proposed launch vehicles and ground segment.2. Utilize standard data and mechanical interfaces between payload and bus, if opting to deliver one or the other, e.g., standard fastener sizes, RS-422, Ethernet, etc. Interfaces may be modified during this effort for concurrent developments.

PHASE III DUAL USE APPLICATIONS: The contractor will pursue commercialization of the various technologies developed in Phase II for transitioning expanded mission capability to a broad range of potential government and civilian users and alternate mission applications.

REFERENCES:1. USA. DoD. GAO. Analysis of Alternatives Is Useful for Certain Capabilities, but Ineffective Coordination Limited Assessment of Two Critical Capabilities. N.p., 10 Mar. 2016. Web. GAO-16-252R

2. Price, Julie. 2015 JPSS Science Seminar Annual Digest. Rep. N.p.: NOAA.gov. Web.

KEYWORDS: Small satellite, cloud imaging, cloud characterization, global coverage, multi-spectral sensor, visible imagery, infrared, IR, near-IR, SWIR, MWIR, LWIR

AF171-074 TITLE: Agile Inspector Satellite

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

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OBJECTIVE: Produce a small space situational awareness (SSA) satellite system with radically high DeltaV. Satellite should exceed 6 km/s of DeltaV to allow significant orbital maneuverability, for example transfer from Low Earth Orbit to Geostationary Orbit.

DESCRIPTION: Spacecraft characterization is a vital component of Space Situational Awareness (SSA) and the U.S. Air Force’s core mission. A desired capability for SSA is the ability to gather resolved images of objects in Geostationary Orbit (GEO). A number of concepts have been proposed for small satellites with imaging sensors that operate in or near GEO that provide adequate imaging resolution by being close to the resident space objects. An enabling capability for such concepts is a high degree of maneuverability in GEO to allow the small satellite to move between the various GEO objects of interest relatively quickly, and/or to transfer quickly between orbits including from Low Earth Orbit (LEO) to GEO.

The cost of achieving spacecraft maneuverability has traditionally restricted satellite CONOPS and mission areas. These limitations originate from insufficient exhaust velocity with chemical thrusters and the relatively high size, weight, and power (SWAP) of satellite systems. The development of highly efficient electric propulsion systems and the corresponding reduction in satellite SWAP, has made achieving extremely high amounts of DeltaV feasible.High DeltaV also makes it possible to leverage the increased availability and affordability of launches to Low Earth Orbit (LEO). A small satellite with sufficient DeltaV could share a relatively inexpensive ride to LEO and subsequently travel to GEO with enough DeltaV remaining to traverse the belt. The efficiency of electric thrusters comes at the expense of thrust. Conducting a low-thrust transfer from LEO to GEO will take several months. Accordingly, the satellite system must be sufficiently radiation hardened to endure a slow trip through the radiation belts.

PHASE I: Conduct system trades to identify an inspector satellite mission concept to provide better than 0.1m resolution imagery of several GEO satellites. Design the satellite with 6 km/s DeltaV capable of surviving a slow journey from LEO to GEO through the radiation belts. Identify appropriate sensor/telescope options, orbital configuration, and downlinks.

PHASE II: Based on the Phase I effort, provide system validation of the mission concept and satellite design. Complete satellite design through critical design review (CDR) and build a ground demonstration unit of the satellite to validate performance. Conduct a hardware-in-the-loop simulation of the system concept to validate system performance.  Model orbital dynamics, subsystem metric, sensor imaging, data downlink, and image processing for a timeline of tasking to tactical image product.

PHASE III DUAL USE APPLICATIONS: The contractor will pursue commercialization of the various technologies developed in Phase II for transitioning expanded mission capability to a broad range of potential government and civilian users and alternate mission applications.

REFERENCES:1. James Szabo, Bruce Pote, Surjeet Paintal, Mike Robin, Adam Hillier, Richard D. Branam, and Richard E. Huffmann.  "Performance Evaluation of an Iodine-Vapor Hall Thruster", Journal of Propulsion and Power, Vol. 28, No. 4 (2012), pp. 848-857.

2. T. Haberkorn, P. Martinon, and J. Gergaud.  "Low Thrust Minimum-Fuel Orbital Transfer: A Homotopic Approach", Journal of Guidance, Control, and Dynamics, Vol. 27, No. 6 (2004), pp. 1046-1060.

3. William A. Hargus, and James T. Singleton.  "Application of Technology Readiness Levels to Micro-Propulsion Systems." 52nd AIAA/SAE/ASEE Joint Propulsion Conference (2016), paper AIAA-2016-5113.

KEYWORDS: small satellite, advanced propulsion, high specific impulse, orbital maneuver, space situational awareness.

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AF171-075 TITLE: Assured Autonomous Spacecraft GN&C via Hybrid Control

TECHNOLOGY AREA(S): Space Platforms

OBJECTIVE: Develop innovative, novel approaches for hybrid mode-logic/discrete-time control/continuous-time physics spacecraft systems that provide mathematically rigorous guarantees of system behavior and performance.

DESCRIPTION: GN&C systems that involve mode-switching logic or gain-scheduling are both examples of a hybrid system, where the dynamics of a finite-state machine (e.g., the mode-logic or the gain-schedule) interact with the dynamics of a continuous-valued system (e.g., the attitude control system & attitude dynamics). State-of-practice for such systems involves rigorous analysis of both the continuous-valued system and the finite-state machine individually via standard techniques. But analysis of the coupled system comprised of the connected mode-logic and control systems is beyond current analysis approaches - regression testing via Monte-Carlo (MC) analysis is the only option, and does not provide rigorous guarantees. Recently, techniques have been published in the literature that allow rigorous analysis of these coupled system behaviors, and in some cases can design coupled mode-logic/control systems with rigorous guarantees for stability and robustness. This SBIR will apply these techniques to missions of AF interest and demonstrate the utility of the resulting set calculations. Techniques of interest include but are not limited to analysis approaches (e.g., linear-temporal logic specification verification via system approximation, bisimulation, model-checking) as well as synthesis approaches (e.g., guaranteed performance via composition or other proofs).

PHASE I: Perform literature survey of methods. Working with sponsor, identify appropriate application example(s) & metrics that methods will be evaluated against. Perform trade study to down-select to one or two algorithms that will form the basis of a Phase-II effort. Document results in a Final Report, and deliver any simulation software to the sponsor.

PHASE II: Develop selected algorithms into suitable software capable of producing results in practical time periods. Develop high-fidelity simulation of application of AF interest with sponsor. Integrate algorithms with simulation to demonstrate utility against metrics. Working with sponsor, examine opportunities for transition of technology to customers of interest.

PHASE III DUAL USE APPLICATIONS: Develop and apply algorithms to specific system of interest to sponsor. Work with sponsor, customer, and associated contractors to integrate algorithms and software into application of interest.

REFERENCES:1. S. Karaman, R. Sanfelice, and E. Frazzoli, “Optimal control of mixed logical dynamical systems with linear temporal logic specifications,” in Decision and Control, 2008. CDC 2008. 47th IEEE Conference on, Dec 2008, pp. 2117–2122.

2. S. Di Cairano, W. Heemels, M. Lazar, and A. Bemporad, “Stabilizing dynamic controllers for hybrid systems: A hybrid control lyapunov function approach,” Automatic Control, IEEE Transactions on, vol. 59, no. 10, pp. 2629–2643, Oct 2014.

3. Tabuada, Paulo. Verification and control of hybrid systems: a symbolic approach. Springer Science & Business Media, 2009.

4. Duggirala, Parasara Sridhar, Mitra, Sayan, and Viswanathan, Mahesh, "C2E2: A Verification Tool For Stateflow Models," In Proceedings of 21st International Conference Tools and Algorithms for the Construction and Analysis of Systems (TACAS) 2015, London

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5. Liu, Jun, et al. "Synthesis of reactive switching protocols from temporal logic specifications." Automatic Control, IEEE Transactions on 58.7 (2013): 1771-1785.

KEYWORDS: hybrid, cyber-physical, verification, validation, control, guidance, attitude, orbital

AF171-076 TITLE: Wideband GPS Digital Payload Architecture

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a Global Positioning System (GPS) transmitter architecture capable of generating the L1, L2, and L5 signals and additional arbitrary signals at discretionary frequencies between 1 and 2 GHz.

DESCRIPTION: GPS broadcasts radio frequency ranging signals at three frequencies: L1 (1575.42 MHz), L2 (1227.6 MHz), and L5 (1176.45 MHz). Multiple signals are modulated onto each frequency, and the nominal bandwidth of each frequency channel is 30.69 MHz. Traditional GPS payloads are comprised of separate transmitters for each frequency, with the RF outputs of each transmitter combined in a multiplexer (triplexer in the case of L1, L2, and L5) and broadcast through a single L-Band antenna.

As digital techniques for RF signal generation have evolved, wideband Direct Digital Synthesis (DDS) supporting bandwidths of tens to hundreds of GHz has been developed for high capacity digital communications. Most of these applications, however, are used at much higher carrier frequencies where a multi-GHz bandwidth is a relatively small fraction of the carrier frequency.For purposes of this topic, consider the GPS Band as the entire range of frequencies that encompasses GPS, from 1161 MHz to 1591 MHz (total bandwidth of 430 MHz). Within the GPS Band are three sub-bands: the L5 sub-band centered at 1176.45 MHz with 30.69 MHz bandwidth, the L2 sub-band centered at 1227.6 MHz with 30.69 MHz bandwidth, and the L1 sub-band centered at 1575.42 MHz with 30.69 MHz bandwidth.

To support experimental L-Band signals, the wideband architecture should also support generation of arbitrary direct sequence spread spectrum signals anywhere from 1 to 2 GHz. These arbitrary signals are for test purposes only, and can be assumed to be similar to GPS signals, although lower in power and with varying chipping rates and signal structure.

Develop a payload architecture to produce signals ranging from 1 to 2 GHz that includes the three GPS sub-bands, in accordance with GPS signal in space interface specifications. Special consideration should be given to complying with out of band emission requirements, which apply to emissions outside of each sub-band. The principle technical questions to be addressed are:1. Does DDS of the entire GPS Band improve the overall efficiency of the GPS payload?2. Are their suitable high-efficiency amplifiers that will provide low-distortion and high gain over the entire GPS Band? Would an alternative amplifier configuration be more suitable?3. Can this approach produce high quality signals with low phase noise, acceptable group delay, and low distortion?4. Can a Wideband GPS Transmitter Architecture support additional signals over the 1-2 GHz range?

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The developer is encouraged to create and implement reference models of the new architecture(s) and the traditional architecture (with separate transmitters) to allow for direct comparison. The desired improvement is 50% reduction of total payload power consumption when delivering minimum signal power as specified in GPS signal in space interface specifications.

PHASE I: Develop an architecture and preliminary design for multi-carrier DDS of the GPS signals, to include waveform generation, filtering, amplification, and other associated hardware. No government materials, equipment, data, or facilities are required for this phase.

PHASE II: Produce breadboard or engineering design model demonstration(s) of multi-carrier DDS and test with L1, L2, and L5 GPS receivers. No government materials, equipment, data, or facilities are required for this phase.

PHASE III DUAL USE APPLICATIONS: Develop DDS payload(s) and implementations of reference PNT (position, navigation, and timing) system architectures, suitable for flight experiment assembly, integration, and test. Commercial: Application to GNSS satellites, GNSS augmentations, and pseudolites.

REFERENCES:1. P. Eloranta, P. Seppinen and A. Parssinen, Direct-digital RF-modulator: a multi-function architecture for a system-independent radio transmitter, in IEEE Communications Magazine, vol. 46, no. 4, pp. 144-151, April 2008.

2. Antoine Diet, Fabien Robert, Genevieve Baudoin, Martine Villegas, Philippe Cathelin, et al., RF Transmitter Architectures for Nomadic Multi-radio: A Review of the Evolution Towards Fully Digital Solutions. Recent Patents on Electrical & Electronic Engineering, 2013, 6 (2), pp.79-94 (16).

3. Ortega-Gonzalez, F.J.; Tena-Ramos, D.; Patino-Gomez, M.; Pardo-Martin, J.M.; Madueno-Pulido, D., High-Power Wideband L-Band Suboptimum Class-E Power Amplifier, Microwave Theory and Techniques, IEEE Transactions on , vol.61, no.10, pp.3712,3720, Oct. 20

4. GPS Interface specifications: IS-GPS-200, ICD-GPS-700, IS-GPS-705, IS-GPS-800.

KEYWORDS: GPS, Direct Digital Synthesis, DDS, wideband transmitter, wideband amplifier

AF171-077 TITLE: Cyber Vulnerabilities & Mitigations in the Radio Frequency Domain

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Identify weaknesses and potential vulnerabilities of embedded system radios to cyber threats.

DESCRIPTION: The United States Department of Defense (DoD) continually designs, acquires, and deploys best in class, highly complex and capable embedded systems. Due to their often high cost, low-density, long development

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time lines, and the mission criticality of the services they may provide, DoD embedded systems have a high value to defense of DoD systems. As we have embraced enhanced embedded system computing capabilities, in most aspects we have become increasingly vulnerable to multiple types of cyber threats.

While vast resources have been invested with the goal of preventing or identifying intrusions and anomalous behavior within our networked enterprise architectures, comparatively little has been done to enhance the mission assurance properties of United States’ real-time, embedded computing systems, if they were to operate in increasingly cyber-contested environments. These systems are subject to customized attack types which target the custom hardware, software and firmware that is frequently found in these systems. State of the art approaches to cybersecurity typically focus only on securing components and end-nodes on the network rather than mission assurance and architectural resilience. When coupled with fundamentally flawed protection schemes common in cyber systems today, this approach creates an ecosystem ripe for potential exploitation. Mission assurance requires levels of prioritization where capabilities become the focus rather than the enabling systems. Furthermore, under stress or duress a resilient architecture will maintain some set of functionality, albeit restricted, to stay in mission and meet some level of mission requirements.

For many real-time, embedded systems used by the DoD, the primary method of communicating information is the radio frequency link and, as such, constitutes a lucrative and exposed cyber and electronic attack surface across the system’s operational life. Major subsystems of the platform, including radios and computers, may exhibit architectural, specification, and implementation vulnerabilities to a variety of RF-enabled cyber methods. The focus of this topic is to develop a library of weaknesses and potential vulnerabilities that might be exploited by adversaries against a variety of radios within the context of real-time, embedded systems.

PHASE I: Perform research and development for the examination of RF-enabled cyber susceptibilities of real-time, embedded system radios, using a Government-furnished commercially-available off-the-shelf (COTS) radio as a case study.Identify a library of weaknesses and potential vulnerabilities.Formulate novel approaches for mitigation, and document in a final report.

PHASE II: On the basis of the Phase I research, conduct in-depth RF-enabled cyber vulnerability assessments on two Government-furnished real-time, embedded system radios.Validate selected and prioritized weaknesses on the provided hardware.As a capstone effort, implement innovative techniques for mitigation.

PHASE III DUAL USE APPLICATIONS: Use the library developed in Phases I and II to conduct a cyber vulnerability evaluation against an assigned embedded system.Provide tool set engineering support to a cyber assessment against an assigned embedded system.Investigate the usefulness of the developed tool for the assessment of existing or in-development commercial systems.

REFERENCES:1. MacDonald, Douglas G. et al. “CYBER/PHYSICAL SECURITY VULNERABILITY ASSESSMENT INTEGRATION.” United States: INMM, Deerfield, IL, United States (US)., 2011. Print.

2. The Science of Mission Assurance. Jabbour, Kamal and Muccio, Sarah. 5, 2011, Journal of Strategic Security, Vol. 4, pp. 61-74.

KEYWORDS: cyber vulnerability assessment, RF-enabled cyber, embedded system cyber security, real-time system cyber security, cyber resiliency

AF171-078 TITLE: SWIR-LWIR detectors employing Unipolar Barrier Architectures

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TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

OBJECTIVE: Experimentally quantify the fundamental performance limits of unipolar barrier architecture infrared detectors through design & fabrication of such devices, and address the question of whether bandgap engineered devices can actually outperform traditional photodetector designs.

DESCRIPTION: There are numerous scenarios where it is necessary to detect optical signals in either the Mid-Wave Infrared (MWIR: 3 – 6 microns) or Long-Wave IR (LWIR: 7 – 12 microns) spectral bands. Currently, mercury cadmium telluride (MCT) is the DoD workhorse that covers these spectral bands due to its high performance, which results from Fresnel-limited internal quantum efficiency and near diffusion-limited dark currents. The option for a heterojunction architecture in MCT results in dark currents that are even lower. The quantum efficiency may be taken to be roughly 65% without an anti-reflection coating, while the dark current is conventionally measured by “Rule 07”, as described in the references. These two metrics will effectively be used as the “signal” and “noise” baselines, against which design solutions will be evaluated.

Detector designs utilizing barriers have been experimentally shown to result in lower dark current than their non-barrier counterparts. Other performance advantages that apply equally well to bulk MCT detectors are of less interest. Thus, high levels of detector performance should be achieved solely by architecture design and should not be restricted to a particular material system, carrier type, barrier number, etc. This SBIR also emphasizes detectors that are optimized for only one spectral band, either MWIR or LWIR, at 80 Kelvin operating temperature; since both these wavelength regions have application for military space-based sensing. Designs employing multiple unipolar barriers, called complementary barrier devices, or multi-height barriers, called compound barrier devices, or any combination thereof, are all relevant to this SBIR. For example, strained-layer superlattice architectures that achieve lower than bulk levels of dark current might be particularly attractive.

PHASE I: The optimum unipolar barrier detector architecture for detecting in the MWIR or LWIR spectrum shall be designed. The detectors will be grown, processed, and, characterized. This shall include at a minimum absorption spectrum, dark current, optical responsivity, and quantum efficiency measurements. The detector will be mounted to a 68 pin leadless chip carrier and provided to AFRL/RVSW for independent characterization of the device. In addition, samples for carrier lifetime measurements should be provided to AFRL/RVSW for independent characterization.

PHASE II: During this phase, the barrier architecture detector will be grown such that it can be processed into a 1024x1024, 18µm pitch detector arrays that will be hybridized to government furnished Read Out Integrated Circuits (ROIC). The functionality of the Focal Plane Array (FPA) shall be demonstrated and thoroughly characterized at light levels reflective of strategic applications. Three (3) working FPA deliverables shall be provided to AFRL for independent radiometric characterization.

PHASE III DUAL USE APPLICATIONS: Commercialization prospects include civil (remote sensing, night vision, intrusion detection) and military (advanced space-based imaging for improved ISR and battlefield awareness) capabilities.

REFERENCES:1. W.E. Tennant, D. Lee, M. Zandian, E. Piquette, and M. Carmody, “Rule ’07,’ Journal of Electronic Materials 37 (9), 1406 (2008).

2. S. Maimon and G. W. Wicks, Appl. Phys. Lett 89 (15), 151109 (2006).

3. W.E. Tennant, “Rule 07 Revisited: Still a Good Heuristic Predictor of p /n HgCdTe Photodiode Performance?” Journal of Electronic Materials Volume 39, Issue 7, pp 1030-1035, (2010).

4. V.M. Cowan, C.P. Morath, J.E. Hubbs, S. Myers, E. Plis, S Krishna, “Radiation tolerance characterization of dual band InAs/GaSb type-II strain-layer superlattice pBp detectors using 63 MeV protons”, Appl. Phys. Lett 101 251108

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(2012).

5. C.P. Morath, V.M. Cowan, L.A. Treider, G.D. Jenkins, J.E. Hubbs, “Proton irradiation effects on the performance of III-V based, unipolar barrier infrared detectors” IEEE Trans. Nuclear Science Volume 62 Issue 2 (2016).

KEYWORDS: Strained-layer superlattice, mercury cadmium telluride, MCT, barrier architecture, sensors, focal plane array, nBn, pBiBn, pBp, space technologies

AF171-079 TITLE: Automatic Exploitation of Energetic Charged Particle Sensor Data

TECHNOLOGY AREA(S): Space Platforms

OBJECTIVE: Automate correlation of incidents of off-nominal spacecraft performance with energetic charged particle drivers to improve space environment anomaly attribution.

DESCRIPTION: New Air Force policy requires Energetic Charged Particle (ECP) sensors on all future spacecraft to enable differentiation between anomalies induced by hostile activity, the natural environment, or other non-hostile causes. It is presently possible to understand the generic space environment hazard to a spacecraft [1], but spacecraft susceptibilities are unique to each design and even to individual spacecraft due to minor variations, workmanship, and on-orbit wear and tear. As local ECP sensors proliferate, the ability to accurately specify the local space particle environment will improve, allowing a more detailed characterization of individual spacecraft susceptibilities to the natural environment. Identifying susceptibilities is presently labor-intensive, requiring a deep understanding of the limitations of the space particle sensors as well as the likely manifestations of anomalies due to environmental drivers. The application of modern data science techniques to the correlation of space environment data from on-board sources with instances of off-nominal behavior will be key to maximizing the utility of ECP sensors in an affordable manner.

The initial goal is to select, tailor and test advanced data processing algorithms against actual space environment data and a corresponding simulated list of spacecraft events that includes a variety of space environment and non-space environment. Characterize the performance of the selected techniques at accurately sorting the environmental from the non-environmental impacts and distinguishing the different environmental drivers. Some level of human intervention may be required to complete the filtering and sorting process, but largely automating the task will provide a useful intermediate step. Demonstration of a path forward towards automation is key. As anomaly lists may have incomplete or inaccurate data in varying formats and ECP sensors may not have uniform capability, accuracy, or cadence [2,3], a solution needs to be robust enough to support probable variation in inputs.

Once the initial goals are complete, the technology should be fully automated, providing analysis across multiple spacecraft or components of the same or similar construction, and generate tailored hazard rules [1] for susceptibility analysis of constellation-level susceptibilities. Develop methods of interacting with supporting automated analysis products, such as automatic anomaly identification and/or hypervisor algorithms.

The ultimate objective is to incorporate the technology into overarching data fusion products for rapid automatic tailoring of environmental susceptibilities. This will entail full interoperability with automated decision support systems such as those deployed as part of satellite operations ground systems or at space battle management command and control systems.

PHASE I: Identify and characterize the performance of data processing algorithms in distinguishing the causes of simulated heterogeneous anomalies using ECP sensor data. Demonstrate capability to provide automation and multi-spacecraft correlation for improved statistical confidence.

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PHASE II: Develop and demonstrate system capable of performing automated multi-spacecraft analysis to develop tailored hazard rules for individual constellations.

PHASE III DUAL USE APPLICATIONS: Demonstrate capability of algorithms to interoperate with spacecraft ground systems in a data fusion environment, supporting rapid automatic tailoring of environmental susceptibilities.

REFERENCES:1. O’Brien, T. P. (2009), SEAES-GEO: A spacecraft environmental anomalies expert system for geo-synchronous orbit, Space Weather, 7, S09003, doi:10.1029/2009SW000473.

2. Dichter, B. K. et. al, Compact Environmental Anomaly Sensor (CEASE): A Novel Spacecraft Instrument for In Situ Measurement of Environmental Conditions, IEEE Trans. On Nucl. Sci., 45(6), 2758-2764, 1998.

3. Lindstrom, C.D. et. al, Characterization of Teledyne microdosimeters for space weather applications, Proc. SPIE 8148, Solar Physics and Space Weather Instrumentation IV, 814806 (September 29, 2011); doi:10.1117/12.89.3814

4. Identifying Environmental Drivers of Satellite Anomalies (uploaded in SITIS on 1/3/17).

KEYWORDS: spacecraft, anomaly, attribution, energetic charged particle, ECP

AF171-080 TITLE: Dual Band Focal Plane Array

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: To develop a dual-band focal plane array EO/IR (0.4 to 2.5 micron) low-size and weight, power and cost (SWaP-C) camera with on-board sensor fusion.

DESCRIPTION: Significant advances have occurred in the development of dual band Infra Red (IR) Focal Plane Array (FPA) technology in recent years. However, current technology often requires multiple FPA's, overly complex optics and significant off board sensor fusion technology in order to meet the needs of missile seekers for next generation smart munitions. Visual navigation will permit platforms like next generation cruise missiles to navigate long distances over featureless terrain when GPS is unavailable. Developed seeker technology will aid in the performance of air launched missiles in varied environmental conditions and in the presence of various obstructions in the imaged scene. Dual band performance will permit visual navigation in day and night conditions. The Air Force seeks innovative solutions for large format, small pixel, dual band Electro Optic (EO) and IR (0.4 to 2.5 micron) camera with high performance, low cost, compact, light weight and low power characteristics.

Acceptable solutions will incorporate efficient real time on board sensor fusion technology to help minimize the need for off board signal processing resources. The offeror will specify achievable focal plane array size given the proposed technology and within typical air launched missile seeker size, weight, power and cost parameters.

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Technologies suitable for new seeker designs as well as those suitable for retrofitting into existing platforms are desired. Offerors with innovative enabling or breakthrough technologies that contribute significantly toward these goals are encouraged to submit proposed technologies if a reasonable path to system development for the described application can be articulated. Innovative technologies that demonstrate reasonable performance in multiple bands will be considered if the engineering trade off with size, weight, power, or other key parameters is significantly advantageous. Any development technology will be suitable for eventual integration into small air launched munitions and cruise missile type platforms.

PHASE I: Phase I entails development of the basic concept of the technology with supported infrared systems engineering modeling and analysis.  It will conclude with a clearly laid out design for a prototype hardware unit.  The technology development plan documented during this Phase will incorporate a feasible path to integrate readout electronics and optics for a full system lab demonstration and field test by the end of Phase II.

PHASE II: Develop and demonstrate a compact prototype of a dual-band focal plane camera unit based on the successful outcome of feasibility assessment determined in Phase I.  A complete dual-band focal plane camera with integral dual bands, (visible and SWIR) optics will be delivered at the end of Phase II.  Show approach to lower unit cost in quantities for small air launched munitions, cruise missile type platforms and commercial applications.

PHASE III DUAL USE APPLICATIONS: Phase III will transition the technology to a fielded platform.

REFERENCES:1. Jay S. Lewis, Nibir K. Dhar, Lee A. Elizondo and Ravi Dat, "Advanced EO/IR technologies at DARPA/MTO," Proceedings of SPIE Infrared Sensors, Devices, and Applications V, SPIE 9609, Sep 2015.

2. Nibir K. Dhar, Ravi Dat, and Ashok K. Sood (2013).  Advances in Infrared Detector Array Technology, Optoelectronics - Advanced Materials and Devices.

3. Prof. Sergei Pyshkin (Ed.), InTech, DOI: 10.5772/51665.  Available from: http://dx.doi.org/10.5772/51665

KEYWORDS: EO/IR, multi-spectral, dual-band, sensor fusion

AF171-081 TITLE: Low-Light SWIR Vision Systems

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop an advanced, high dynamic range vision system concept, processing techniques, and hardware for sensing the environment in the SWIR wavelengths under both regular and photon-limited conditions.

DESCRIPTION: Develop an advanced, high dynamic range vision system concept, processing techniques, and hardware for sensing the environment in the SWIR wavelengths under both regular and photon-limited conditions.

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The SWIR wavelength is rich in visual information that can support a variety of tasks. Night-time airglow is substantially stronger in these wavelengths than in the visible spectrum, providing more ambient illumination for vision systems operating outdoors. General techniques for sensing in these wavelengths include photodiode arrays fabricated in a semiconductor material such as InGaAs that are hybridized with silicon readout integrated circuits (ROICs). The performance of such systems is generally limited by a high dark current inherent in such materials. It is desirable to extend the bottom range of light levels over which systems can operate, to allow usage in environments further removed from outdoor ambient illumination, such as inside buildings and caves, and deep beneath forest canopies. This would extend the range which platforms carrying these vision systems can operate stealthily without giving themselves away by artificial illumination. Thus the goal of this topic is to develop a high dynamic range vision system, operating primarily in the SWIR band, and able to operate in all light levels ranging from several photons per photodetector per second up to daylight conditions.

PHASE I: Develop the concept and create a preliminary design. Build a breadboard to test and demonstrate the viability of the concept.

PHASE II: Complete the final design, then build and test the prototype for delivery.

PHASE III DUAL USE APPLICATIONS: Partner with industry to develop prototype system into a commercial product

REFERENCES:1. M. Dandin and P. Abshire, High Signal-to-Noise Ratio Avalanche Photodiodes With Perimeter Field Gate and Active Readout, IEEE Electron Device Letters, 33 (4): 570-572, April 2012

2. E. Warrant and M. Dacke, Vision and Visual Navigation in Nocturnal Insects, Annual Review of Entomology, Vol. 56, pp. 239-254, January 2011

3. M. Massie and J. Curzan, Demonstrated Neuromorphic Infrared Hybrid Focal Plane and a Vision of the Future, SPIE Vol. 2269, 1994

4.https://en.wikipedia.org/wiki/Airglow

KEYWORDS: SWIR, night operations

AF171-082 TITLE: Modeling and Simulation of Complex Multiphase Interaction of Energetic Materials

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop algorithms for predicting the physics and effects of non-traditional blast events, such as multiphase blast events. Algorithms that can be implemented within existing computer simulation tools such as

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CTH or ALE3D are preferred.

DESCRIPTION: The performance (i.e. range, agility) of next generation missile systems needed for Air Superiority may be increased by altering typical volume allocations. Agility and range may be increased at the expense of the volume allocated to an ordnance payload but the payload must be effective. Significant reductions in conventional payloads impose increased performance requirements on the seeker and target detection device. These increased performance requirements may be alleviated by generating more effective lethal energy from smaller systems to account for the reduction in volume. If a payload is a quarter of the conventional volume but its energy release and lethality is similar to the conventional system then the advantage of increased range and agility may be achieved without increased demand on the seeker and target detection device. Within the last decade test data has been generated that examined the effect of coupling focused detonation shock-waves within high explosive (HE) to structural reactive materials and the data indicate the pressure and corresponding impulse can be increased compared to a traditional configuration. In order to understand the phenomenology and exploit its potential, models must be created that bridge the gap between explosive reactive flow models that capture detonation wave propagation and models that capture slower energy release such as the energy release of burning propellants. Controlling the energy release rate of reactive materials containing greater potential energy than explosives requires understanding the kinetics involved in the energy release process. Attempts at understanding the ignition and burn rate of reactive materials are being pursued at the academic level. A multi-component, multi-phase mixture theory has been used by Koundinyan et. al. to describe the ignition of multi-material condensed phases such aluminum/copper-oxide and titanium-boron. This technique needs to be explored and further understood since it represents a pathway for achieving a more lethal effect from smaller ordnance payloads which is required by the applications addressing the Air Superiority capability area. Additionally, the technique implies a selectable output capability since thereactive material may not be loaded to the necessary conditions and therefore release less energy. Proper exploitation of the phenomenon would have ramifications to a wide range of munitions which would benefit from an option to exploit a maximum or minimum response from the same munition.

PHASE I: Assess feasibility of initial subroutines to generate simulation results that show predictive capability of complex, shockwave interaction between an explosive and structural reactive material. Predictive capability will be assessed using existing test data.

PHASE II: Demonstrate predictive capabilities that can incorporate either non-reactive multiphase blast, or some reactive chemical kinetics, or possibly both in the modeling and simulation of a detonation event(s). Predictive capabilities will be systematically assessed through parametric, sensitivity study and validated with test data.

PHASE III DUAL USE APPLICATIONS: Implementation of validated algorithms within commonly used first principles based computational codes (i.e. CTH, ALE3D). Validation of predictive capability through demonstration test of an explosive/reactive material configuration that has been designed using the algorithms/methodology.

REFERENCES:1. Lee Hardt, NAWCWD; Claude Fore, Joseph Vaughan, Sean Martinez, ITT Information Systems. (April 2011). Final Test Report, MIDWAY TEAL Tests 1-44. DTRA FTR-10-019, Distribution Statement D

2. Stewart, S., Glumac, N., Foster, J., Investigations on Explosive Systems with Controllable and Variable Energy Release and Blast, Office of Naval Research and NAVAIR, China Lake: Final Report for N00014-08-1-0848.

3. Koundinyan, S. Bdzil, J., Matalon, M., Stewart, S., Diffusion flames in condensed-phase energetic materials:Application to Titanium-Boron combustion, Combustion and Flame, vol. 162, 2015, pg 4486-4496

4. Koundinyan, S., Lee, K., Murzyn, C., Clemenson, M., Glumac, N., Stewart, S., Theoretical and Experimental Investigations of Fast Ignition/Quenching in Al/CuO Thermite, unpublished prepreprint draft. (Updated in SITIS on 02/02/17)

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KEYWORDS: Multi-phase blast, multi-phase by-product interaction, HMX, RDX, CL-20, multi-phase explosive, reactive materials

AF171-083 TITLE: High-g MEMS Accelerometer Sensor for Hard Target Applications

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a low cost SWAP replacement for the current MEMS accelerometer sensor in the Hard Target Void Sensing Fuze (FMU-167).

DESCRIPTION: Low-cost microelectromechanical system (MEMS) based accelerometers have steadily progressed in the commercial applications. Some of these sensors have been tested for military applications with limited success, and offer a low cost alternative. However, to achieve the required performance for the MEMS accelerometer sensors for the military applications a robust basic research is warranted in the science of MEMS sensor formulation itself. The key areas of research are sensing mechanism(s) for the acceleration vector and robust electrical circuit topology and formulation(s) for the transduction process.

Examples of military applications of high-g MEMS sensor include: hardened bunker layer thickness estimation, voiddetection and counting, and munitions developmental test (DT) and operational test (OT). The following parameters should be considered: Robust (Shock Survivable, >90kg), Small Size, <0.01 in3, Low sensitivity to other variables (i.e. pressure induced acceleration), Adequate linear bandwidth (>100kHz), Low Cost.

PHASE I: Perform survey of current state-of-the-art for high reliability, high-g accelerometers. Perform preliminary analysis and conduct trade studies to identify a suitable MEMs design for a low cost solution to high reliability high-g accelerometers as applied to the dynamic modes of large projectiles.

PHASE II: It is expected that the Phase I concepts will be matured and demonstrated in actual fabrication experiments involving at least two potential designs. These designs will be tested in a relevant high-g environment that contains peak, duration, temporal and spectral content to demonstrate functionality, reliability, and robustness. It may be necessary to test at a Government facility to achieve the necessary environment.

PHASE III DUAL USE APPLICATIONS: Design demonstrated in phase II will be integrated in to a higher-order assembly such as a data recorder for application in a projectile in a high-g environment.

REFERENCES:1. J. C. Dodson, L. M. Watkins, J. R. Foley, and A. L. Beliveau, Comparative Analysis of Triaxial Shock Accelerometer Output, in Structural Dynamics, Volume 3, T. Proulx, Editor 2011, Springer New York. p. 1529-1536.

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2. J. C. Wolfson, J. Foley, A.L.Beliveau, G. Falbo, J. Van Karsen, Pyroshock Loaded MISO Response, in Modal Analysis Topics, Volume 3, T. Proulx, Editor 2011, Springer New York. p. 533-539.

3. J.C. Wolfson, J.R. Foley, L.M. Watkins, A.L. Beliveau, P.C.Gillespie, Modal Testing of Complex Hardened Structures, in Structural Dynamics, Volume 3, T. Proulx, Editor 2011, Springer New York. p. 1481-1487.

KEYWORDS: MEMS, terra-navigation, high-g, deceleration, acceleration, reliability, low-cost

AF171-084 TITLE: Advanced Bio-inspired Imaging System with Multiple Optical Sensing Modes

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: To develop a multi-spectral EO/IR sensor to enhance target identification and clutter/obfuscation rejection.

DESCRIPTION: The US Air Force has a need to develop an imaging system for seeker and ISR applications requiring enhanced target identification and clutter suppression using multiple simultaneous optical sensing modes. The system architecture can take inspiration from a variety of arthropods capable of viewing prey, mates, and their environment using several optical bands and polarization schemes. For example, some stomatopods are capable of viewing through 12 spectral bands while simultaneously sensing linear and circular polarization.The desired imaging system will sense the entire Field of View through at least 4 spectral bands and all 4 polarization components of the Stokes vector, simultaneously, without the need for a time-dependent scan across optical sensing modes or the image scene. Spectral bands can be anywhere from UV to LWIR, but since military utility is increased with nighttime imaging capability, not all of the bands should be visible wavelengths. The entire image scene will be available / displayable in any one of the optical modes or combination of modes. The goal is to find a solution more robust than conventional Division of Focal Plane filter and polarization schemes, wherein a mosaic of pixel sized filters and polarizers are laid across the sensor. These types of filtering/polarizing schemes are discouraged because they are inefficient, and they tend to generate interpolation errors and moiré patterns when viewing high resolution targets.

PHASE I: During Phase 1, develop the concept, including spectral bands of interest and polarization scheme, and create a preliminary design. Identify materials to realize the polarization scheme. Build a breadboard to test the viability of the concept.

PHASE II: During Phase 2, complete the final design, then build and test the prototype for delivery.

PHASE III DUAL USE APPLICATIONS: During Phase 3, partner with industry to develop production quality system for insertion into appropriate military program and/or commercial market.

REFERENCES:

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1. Goldstein D. H., “Polarization Properties of Scarabaeidae,” Appl. Opt. 45, 2006, pp. 7944-7950.

2. Myhre G., Sayyad A., Pau S., “Patternable color liquid crystal polarizer,” Optics Express 18, 2010, pp. 27777-27786.

3. Tyo J. S., Goldstein D. L., Chenault D. B. and Shaw J. A., “Review of passive imaging polarimetry for remote sensingapplications,” Appl. Opt. 45, 2006, pp. 5453-5469.

4. Myhre G., Hsu W. L., Peinado A., LaCasse C., Brock N., Chipman R. A. and Pau S., “Liquid crystal polymer division of focal plane polarimeter,” Optics Express 20, 2012, pp. 27393-27409.

KEYWORDS: multi-spectral, EO/IR, sensor

AF171-085 TITLE: Small Munitions Advanced Seeker Handoff (SMASH)

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: To integrate national ISR and satellite into a real-time target identification and targeting network for weapons cueing and control

DESCRIPTION: Next generation Air Force weapons will need to negotiate highly contested spaces. They will require fusing of information from multiple sources to include low cost on-board and off-board sensors and compressed data from space-based or other ISR platforms. The AF desires novel concepts for handing off, transmitting, fusing and processing of such multi-modal data. Concepts may include compact target representations that can be generated by the ISR sensor and then succinctly transmitted to the weapon seeker to help the weapon reacquire the target. Other concepts may include using the ISR / satellite system to automatically generate predictive models of the target as it would appear in the weapon seeker domain followed by transmission of the predictive model over a weapon network to the weapon seeker. Concepts may include new high bandwidth weapon data link technology, novel sensor fusion and compressed sensing concepts such as finding methods to transform target representations found with the ISR sensor into target representations that the weapon sensor would see. This would include ISR / weapon sensors that are the same modality and ISR / weapon sensors that are different modality. This may draw significantly from ideas for generating models of targets in one domain using information acquired in a different domain. The AF anticipates the developed capabilities will be crucial for successful terminal guidance of next generation cruise missiles and similar highly interconnected small munitions. Developed concepts must include estimates of the network bandwidth, topology, etc. that would be required for implementation of any proposed concepts.

PHASE I: Design a concept to enable automated cueing of a weapon seeker using target or scene context information gathered by an airborne or space-based ISR platform. The concept could involve the transmission of

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target or scene context information extracted from the ISR / satellite data or transmission of a predictive model of the target signature as it would appear in the weapon seeker sensor domain.

PHASE II: Continue developing and assessing the technical merit, feasibility, and commercial potential of the proposed concept. Design and construct a system to demonstrate the proposed automated weapon seeker cueing function. Design and construct simulations of external sub-systems necessary to demonstrate the overall operational concept. Develop a test plan and methodology to demonstrate and evaluate the value of the proposed concept. Conduct the demonstration and evaluation using relevant data.

PHASE III DUAL USE APPLICATIONS: Continue development of the proposed concept in cooperation with potential technology transfer or commercialization partners.

REFERENCES:1. "Visual domain adaptation: A survey of recent advances," Patel, V.M., Gopalan, R., Li, R., and Chellappa, R., IEEE Signal Processing Magazine, Vol. 32, Issue 3, May 2015, pp. 53-69. http://citeseerx.ist.psu.edu/viewdoc/download?doi=10.1.1.445.2867&rep=rep1&type=pdf

2. "Autonomous target handoff from an airborne sensor to a missile seeker," Kossa, L.E., and Tisdale, G.E., Proceedings of SPIE 0219, Electro-Optical Technology for Autonomous Vehicles 142, 24 April 1980.http://proceedings.spiedigitallibrary.org/proceeding.aspx?articleid=1229726

3. "Real-time targeting for network enabled weapons," Frame, S.R., ITEA Journal 2010, Vol. 31, pp. 316-320, http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA530388

4. "NEW: Network-Enabled Electronic Warfare for Target Recognition," Liang, Q., Cheng, X., and Samn, S.W., IEEE Transactions on Aerospace and Electronic Systems, Vol. 46, Issue 2, April 2010, pp. 558-568.

5. "Signature prediction for model-based automatic target recognition," Keydel, E.R. and Lee, S.W., Proceedings of the SPIE 2757, Algorithms for Synthetic Aperture Radar Imagery III, 306 (June 10, 1996), http://proceedings.spiedigitallibrary.org/proceeding

KEYWORDS: Network Enabled Weapon, weapon cueing, transfer learning, domain adaptation, machine to machine, M2M, signature prediction, signature modeling, context, contextual cueing

AF171-086 TITLE: Full-size Warhead Computed Tomography

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Augment existing munition X-ray facility to perform computed tomography

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DESCRIPTION: The warheads in future munitions are expected to grow in complexity and contain materials and components with a wide range of densities (20 - 0.6 g/cc). The Air Force is therefore interested in techniques that can extend the utility of conventional 2-Dimensional (2D) X-ray facilities suitable for imaging full size warheads (i.e. a pulsed 3.5 or 6 MeV X-ray source) by augmenting it with automated sample manipulation, image collection/indexing, and computed tomography (CT) capability.

PHASE I: Design appropriate experimental, diagnostic techniques, and computational methods adapting a pulsed, high-energy (3.5 -6 MeV) X-ray head to obtain CT images of full-scale warheads containing components with a large range of densities. Methods shall include the ability to operate in high resolution (slow) and low resolution (fast) modes.

PHASE II: Develop and implement the designs and techniques from Phase I. Characterize representative scales that demonstrate the suitability of the technique at obtaining CT images of large scale (5000 lbs class) warheads as well as small scale (~250 lbs class) systems and maintain the required resolving power.

PHASE III DUAL USE APPLICATIONS: This technology is applicable to the nondestructive evaluation of a wide variety of systems containing energetic materials and propellants of interest to the Air Force and DoD. Commercial interests may include devices utilized in mining, rocket propellant, and medical industries.

REFERENCES:1. M. Salamon, M. Boehnel, N. Reims, G. Ermann, V. Voland, M. Schmitt, N. Uhlmann, R. Hanke, Applications and Methods with High Energy CT Systems, Proceedings of the 5th International Symposium on NDT in Aerospace, 13-15th November 2013, Singapore

2. A. Flisch, P. Schutz, T. Luthi, M. Plamondon, J. Hofmann, I. Jerjen, High energy CT with portable 6 MeV linear accelerator, Proceedings of the 5th Conference on Industrial Computed Tomography, 25-28 February, 2014, Wels, Austria

3. R. Kaufmann, A. Flisch, M. Griffa, S. Hartmann, J. Hofmann, I. Jerjen, Y. Liu, T. Lüthi, A. Neels, M. Plamondon, F. A. Reifler, P. Schuetz, C. Stritt, F. Yang, A. Dommann, New Directions in X-ray Tomography, Proceedings of the 11th European Conferenc

KEYWORDS: X-ray, warhead, munition, XCMT, CT Scan, Computed tomography, non-destruction evaluation

AF171-087 TITLE: FRM Automated Development (FAD)

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop an automated software methodology that can reduce the overall time, costs, & complexity associated with the development of fast-running response models for the structural & infrastructure components of

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urban structures.

DESCRIPTION: This topic aims to develop a new software methodology capable of creating accurate, expandable, and adaptable High-Fidelity Physics-Based (HFPB) Fast-Running Models (FRMs) for use in weapon-target interaction (WTI) studies. The current approach to developing HFPB FRMs is to employ either physical data or the results from validated HFPB computational models as surrogate data to correlate target response to weapon loads and then formulate FRMs based on this data as fixed software modules to predict WTI responses, compute metrics for uncertainty quantification (UQ), and then validate the FRMs with data suitable for validation. This process has been very successful on a case-by-case basis, such as when addressing a new building component or infrastructure item. However, this process requires a very high-level of expertise to produce any one FRM for different target materials or component types for which a more rapid development cycle is needed to meet emerging testing and mission needs. Considering the broad range of targets (components ranging from columns, beams, walls, floors, etc.), target materials (steel, concrete, brick, adobe, stone, wood, etc.), infrastructure (power, telecom, pluming, HVAC, etc.) weapons (inventory and developmental), and secondary effects that can be generated during WTI (secondary debris & airblast, gas pressure, venting, etc.), a new methodology capable of generating FRMs that can be run by government personnel is desired.

Consequently, development of a highly automated software model capable of producing HFPB FRMs that can supplement the existing ones for broader or emerging ranges of targets is required. The methodology must address loading from weapons effects that include airblast, gas pressure, weapon fragment and structural debris loadings, and time-dependent variable venting. The resulting software model will need to be integrated into AFRL’s Modular Effectiveness Vulnerability Assessment (MEVA) software architecture to provide seamless transitions between the existing single-strike FRMs and new progressive-damage methodology, require a level of expertise consistent with an analyst familiar with weapons effects and target response, potentially having access to Verification and Validation (V&V) data, and yield HFPB FRMs that have execution times similar to the existing FRM(s). Desired FRM outputs include structural component damage (deflection, spall, breach, and/or failure), structural debris mass & velocity distributions, subsequent residual strength (residual capacity), and Collateral Damage Estimation (CDE) data.

One of the options for defeating urban structures is collapse due to damage from single or multiple weapons. Walls, columns, beams, and slabs not completely destroyed during a strike could be further damaged during subsequent strikes to promote structural collapse. The residual capacity of the structural components under repeated weapon loading, including impulse loading from structural debris and secondary airblast, is of interest. These residual capacity outputs will be fed into a progressive collapse model to determine the structural integrity of the building.

Current requirements specify the need for FRMs that predict the damage to Urban Mass & Framed constructed structures (subjected to single or multiple weapon detonations at single or multiple locations) with an overall accuracy of 80% or better when compared to actual test data. Blast & fragment loads from current & future weapons are of particular interest. If necessary, government test facilities and or test data will be provided if requested and within the government’s funding constraints. If required, government HPC facilities will be provided to the contractor upon request.

PHASE I: Develop a.) a theoretical approach to model development & uncertainty quantification, and b.) a software approach, that together will yield a tool that can automate the steps in the production of HFPB FRMs. Demonstrate the approach using a simplified structural component item and an infrastructure component. Document the efficiency & potential cost savings and develop a Phase-II prototyping plan.

PHASE II: The contractor will develop the standalone software (operated in an off-line mode). The software will allow analysts & target/weapon experts to select data for a variety of structure & infrastructure components, select the desired output responses, and then the range of loads from AF weapons. Next, the software will automatically calculate the training data covering the range of problem parameters. Lastly the software will utilize the training data to train the fast running models.

PHASE III DUAL USE APPLICATIONS: Military Applications: A wide range of lethality assessment programs throughout the DoD rely on legacy damage severity models. Using HFPB models is extremely costly in terms of

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data development and computational cost. This streamlined ability for analysts to develop FRMs is what is needed.

REFERENCES:1. Reference 1: Crawford, J.E., and H.J. Choi, "Development of Methods and Tools Pertaining to Reducing the Risks of Building Collapse," Proceedings of the International Workshop on Structures Response to Impact and Blast, November 2009, Haifa, Israel.

2. Reference 2: Lloyd, G.L., T. Hasselman, and J.M. Magallanes, "Fast Running Model for the Residual Capacity of Bomb-Damaged Steel Columns," Proceedings of the 80th DDESB Explosives Safety Seminar, Palm Springs, CA, August 12-14th, 2008.

3: Anderson, Mark C., W. Gan, and T. K. Hasselman, "Statistical Analysis of Modeling Uncertainty and Predictive Accuracy for Nonlinear Finite Element Models," Proceedings of the 69th S & V Symposium, Minneapolis/St. Paul, Minnesota, October 12-16, 1998.

KEYWORDS: High-fidelity physics based simulations, simulation, weapon target interaction, fast running models, reduced order models, surrogate models

AF171-088 TITLE: Reactive Composite Materials for Asymmetric Shock Propagation in Multi-Functional Weapons

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop material solutions that can provide enhanced lethality and selectable energy outputs from mitigated, attenuated or directional shock propagation.

DESCRIPTION: Weaponization of current and future air platforms will require smaller munitions with equivalent or better lethality than today’s weapons. One possible solution is the development of highly flexible ordnance packages that can provide a range of lethal effects. This could include multi-functional systems that provide penetration, area attack and low collateral damage capabilities within a single weapon or half penetrating, half fragmenting warheads. Other possibilities are decoupling fragments from the main charge or the ability to reduce the velocity of designated frags. Such munitions could allow the prosecution of a wider range of targets through the synchronization of selected effects. Conceivably, these capabilities can be better achieved by using liners/barriers within the weapon that are capable of mitigating or attenuating shock propagation in one direction versus the opposite. These materials would most likely be engineered composites with highly anisotropic properties.

The intent of this topic is the design and development of multi-functional composites capable of controlling energy outputs through a finite thickness by intentionally affecting the intensity of propagating shock waves in one direction while accelerating or allowing its unimpeded progress in the opposite direction. This could include changing/restricting the path or direction (i.e. propagation in one direction, but not the opposite direction) or modifying the attenuation characteristics (i.e., dampening/reduction below critical threshold) through impedance

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mismatching, energy absorbency, morphological design, or a combination thereof. Studies have shown the potential of tailoring shock propagation through layered structures with foams cores, liquids in elastic shells, cellular materials, abrupt geometrical changes, introduction of dust particles, interlaced molecular threaded polymers, etc. Enhanced blast effects should be achieved through the addition of chemical energy to the detonation event using materials such as thermites and intermetallic systems. Reduced munition sizes will require a full exploitation of all subsystems and therefore multi-purposed materials with tailored architectures are desired. Proposed solutions should specifically address energetic and shock properties and should take into consideration application environment and limited area available for insertion. Numerical and experimental analysis should be performed to demonstrate predicted efficiency of proposed materials in controlling waves properties (i.e. shock speed, arrival time, maximum peak pressure, etc.) and specific mitigation strategy should be identified.

PHASE I: Design multi-functional materials that provide enhanced blast and controllable wave propagation capabilities and develop efficient techniques to fabricate these designs. Perform computational analysis to predict wave propagation properties of proposed materials. Small scale fabrication to show manufacturing feasibility is highly desirable.

PHASE II: Develop, demonstrate and validate concept developed in Phase I. Deliverables are a prototype demonstration, experimental data, 1x1 samples, a baselined model with experimental data, and substantiating analyses. Incorporate lessons learned and scale-up material concept.

PHASE III DUAL USE APPLICATIONS: The military application is ordnance. Commercial application could include sports and law enforcement personal protective gear.

REFERENCES:1. O. Igra, J. Falcovitz, L. Houas, and G. Jourdan, Review of methods to attenuate shock/blast waves, Progress in Aerospace Sciences 58 (2013) 1-35.

2. E. Gutierrez-Puebla, Interlacing molecular threads, Science 351 (2016) 336.

3. J-W Park, J-S Kim, Feasibility of shock attenuation by simple obstacles in mitigating severe accident explosive loads, Annals of Nuclear Energy 70 (2014) 109.

4. W. Chen, H. Hao, S. Chen, F. Hernandez, Performance of composite structural insulated panel with metal skin subjected to blast loading, Materials and Design 84 (2015) 194.

5. N. Gardner, E. Wang, P Kuma, A Shukla, Blast mitigation in a sandwich composite using graded core and polyurea interlayer, Exp. Mech. 52 (2) 119.

KEYWORDS: asymmetric shock propagation, attenuated shock, shock mitigation

AF171-089 TITLE: High Voltage (HV) Fireset Systems and Subsystem Component Level Designs

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors

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are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop super low inductance HV Fireset System, focused on enhanced performance for CDU switches and HV capacitors subsystem technology with very low ESR, high peak current capability, and ultra-fast di/dt current rates operating from 1kV to 60kV.

DESCRIPTION: Both the DoD and DoE explosive research community heavily rely upon high voltage (HV) Fire-set and Pulsed Power Systems to conduct detonation transfer reliability research to characterize the performance of explosive trains for future Air Force (AF) weapon systems. In addition, the described research is strongly tied to developing high fidelity hydro-code numerical models of detonation trains, which provides tremendous cost-savings when it comes to weapon and experimental design implementations.

Furthermore, HV Fire-set systems are used for initiation studies to discharge large amounts of energy at ultra-fast di/dt current rates into Explosive Foil Initiators (EFIs) to quantify detonation transfer performance of various flyer materials, geometries, and thicknesses into insensitive munition (IM) booster materials. Within the Air Force Research Lab, it has been discovered with their current HV fire-set systems that HV capacitor discharge unit (CDU) capacitance & CDU switch performance is a critical technology base that needs refined development, and is a significant contributor to the overall performance reliability and repeatability of these systems. More importantly, the available energy, energy transfer efficiency, and peak current transfer rate of the HV Fireset system allows for optimum flyer velocities to be achieved. The advancement of CDU switch, HV capacitor, and trigger technologies may vastly expand the DoD’s and DoE’s capability to conduct more robust experiments in controlling the resolution of achieving various flyer velocities. As a result, higher fidelity data sets can be attained to improve our understanding for detonation train performance and foster robust and reliable designs for future DoD weapon systems.

Key HV Fireset System design problems are prevalently associated with deficiencies in inductance, energy density transfer, and di/dt rates within the overall electrical performance limited by CDU switch performance & HV capacitor parasitic inductance. Development efforts should focus on leveraging both existing HV Pulsed Power switch and capacitor technologies. Switch technologies considered for Fireset integration may include spark gaps, rail gaps, and surface planar discharge gap switches that are either electrically or optically triggered, with consideration for other state of the art options. Additionally, the proposers are encouraged to investigate the various cathode, anode, potting, and dielectric insulating materials, implemented for future designs to significantly decrease inductance, increase the life cycle, and ease of maintenance for both switch & capacitor technology. A suite of HV capacitor & CDU switch design solutions to cover various ranges of operating voltages are acceptable, with the goal to achieve the widest range as possible to achieve super high peak current outputs at ultra-fast di/dt current transfer rates. Ideally, the proposers should have extensive expertise in HV pulsed powered system & capacitor design.

PHASE I: Investigate state of the art HV switching and capacitor technologies to improve overall performance of conventional fireset systems. Develop an initial design concept of a HV Fireset system that will be used to characterize performance capabilities for EFI technologies specified by the Air Force Research Laboratory. The design concept should be validated by an electrodynamic multi-physic code.

PHASE II: Develop and construct a prototype design of a proposed system from phase I. Perform laboratory bench level experiments to demonstrate the performance of the fireset system design. Establish operating voltage range along with the entire systems lump sum R, L, & C parameters including the output load representative to an EFI. In addition, provide ring down and load current waveforms at the various operating voltages and load conditions.

PHASE III DUAL USE APPLICATIONS: The DoE and DoD will benefit from the utilization of highly optimized fireset systems, which will advance capabilities to test EFIs beyond conventional energy levels. As a result, extensive experimentation may be performed for advanced detonation transfer studies of novel IM and EFI technologies

REFERENCES:

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1. H. Chau, G. Dittbenner, W. Hofer, C. Honodel, D. Steinberg, J. Stroud, R.Weingart and R. Lee, "Electric Gun: A versatile tool for high-pressure shock-wave research," Review of Scientific Instruments, vol. 51, no. 12, pp. 1676-1680, 1980.

2. R. C. Weingart, R. K. Jackson and C. A. Honodel, "Shock Initiation of PBX-9404 by Electrically Driven Flyer Plates," Propellants and Explosives 5, pp. 158-162, 1980.

3. HV SBIR Helpful Notes on Baseline Technical Specifications (Uploaded in SITIS on 01/19/17)

KEYWORDS: HV Pulsed Power, HV Pulsed Power Discharge Capacitor, HV Fireset, HV Electric Gun, Capacitor Discharge Unit Switch, Sparkgap, CDU Switch Technology

AF171-090 TITLE: Deep Learning Tools and Architectures for Munitions (DeLTA-M)

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Apply recent advances and develop innovative solutions in deep learning techniques to support future autonomous weapons.

DESCRIPTION: Next generation weapons will incorporate increased levels of autonomy. They will require rapid critical decision making based on limited sensory inputs while ensuring high levels of trust. The AF desires deep learning architectures, analytical tools to evaluate machine learning architectures and technologies as applied to weapon navigation, control, multi-modal information processing, target evaluation, and other air-launched weapon functions.

Offeror will use advances in nonlinear dynamics theory to characterize and understand deep learning networks or other machine learning architectures. Innovative solutions incorporating dynamic learning, efficient hardware design and high levels of trust are a priority. Proposed solutions will focus on particular applicability to air-launched weapons. Approaches incorporating weapon cooperation, multi-modalities and multi-sensor compressed data fusion are acceptable. Offeror will develop a prototype machine learning architecture and evaluation toolset suitable for integration into AF weapons and weapon development.

PHASE I: Phase I will entail development of the basic concept of the deep learning technology with supported modeling or analysis. It will conclude with a clearly laid out design for prototype deep learning architecture for munitions and toolset specifications.

PHASE II: Phase II will result in a developed deep learning architecture and toolset using the design generated in Phase I.

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PHASE III DUAL USE APPLICATIONS: Phase III will transition the technology to an appropriate platform.

REFERENCES:1. Schmidhuber, J., "Deep Learning in Neural Networks: An Overview," Neural Networks, V. 61, Elsevier, Jan. 2015.

2. LeCun, Yann, Yoshua Bengio, and Geoffrey Hinton, “Deep learning,” Nature521, no. 7553, 2015, pp. 436-444.

3. Ciresan, Dan, Ueli Meier, and Jürgen Schmidhuber, “Multi-column deep neural networks for image classification,” Computer Vision and Pattern Recognition(CVPR), 2012 IEEE Conference on, IEEE, 2012.

4. Marc’Aurelio Ranzato, Y., Lan Boureau, and Yann LeCun, “Sparse feature learning for deep belief networks,” Advances in Neural Information Processing Systems, vol. 20, 2007, pp. 1185-1192.

KEYWORDS: deep learning, neural networks, dynamic learning

AF171-091 TITLE: Corrosion Indicating Coatings for Aircraft Bilges and Wheel Wells

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop a coating for application in aircraft bilge and wheel well locations that will change color upon corrosion of substrate, indicating where corrosion maintenance needs to be performed.

DESCRIPTION: Bilge and landing gear wheel well locations are considered severe corrosion environments on aircraft. Bilges of transport aircraft are exposed to contaminants leaked from cargo, such as sand and salt laden support equipment, tanks, etc. Additionally, any leaks from lavatory or other moisture intrusion settle into bilge locations. Landing gear are exposed to corrosive elements from runway debris and conductive runway deicers, and suffer impact damage which can serve as initiation spots for corrosion. To facilitate inspections for hydraulic leaks and other maintenance, these locations are painted gloss white for visibility. However, corrosion develops underneath these locations and is difficult to assess, until significant corrosion has already occurred. A coating for these locations that changes color upon initial corrosion would enable maintainers to identify and repair corrosion, before it becomes too severe and costly to repair. The color change must result from corrosion, not just changes in pH, as temporary changes in pH do not by itself necessarily result in corrosion. This coating shall be qualified to either MIL-PRF-85285 or MIL-PRF-32339 at the end of Phase III. The use of government materials, equipment, data, or facilities can be accessed through the existing CRADA.

PHASE I: Develop prototype coating system, including topcoat and specific primer, if required, that will change color from white to another color readily identifiable by maintainers as requiring maintenance, when corrosion occurs on substrate. The color change cannot be on pH alone. Demonstrate coating color change in comparison to baseline MIL-PRF-85285 gloss white coatings under salt fog evaluation.

PHASE II: Perform long-term outdoor exposure as described in MIL-PRF-32239 to evaluate long-term corrosion performance of Phase I developed coating. Demonstrate reparability of coatings where the coating used in the repaired area corrosion at the same level the original coating performed. Demonstrate compatibility of coatings with Air Force maintenance chemicals.

PHASE III DUAL USE APPLICATIONS: Working with AFLCMC/EZP, identify testing required to transition technology across Air Force weapon system platforms. Perform coatings testing on all substrate materials identified,

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and qualify coating to MIL-PRF-23377/MIL-PRF-85285 or MIL-PRF-32339 as required.

REFERENCES:1. http://corrosion.ksc.nasa.gov/.htm.

2. https://researchnews.osu.edu/archive/pnkpaint.htm.

3. http://www.corrosion-club.com/smart.htm.

KEYWORDS: bilge, color change, corrosion, paint, wheel well

AF171-092 TITLE: Coating Additives for Enhanced Laser De-paint

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Incentivize small business to develop additives that can be integrated into currently qualified aerospace coating systems (primers and/or topcoats) to regulate strippability with near-infrared (IR) laser systems. The coating systems with the additives included shall be qualified to either MIL-PRF-23377, MIL-PRF-85285, MIL-PRF-32239, TT-P-2760, or MIL-P-81733. Additionally, the proposed additives cannot result in coatings with higher environmental, safety or occupational health risks than the current coatings.

DESCRIPTION: USAF aircraft are currently coated with epoxy primers qualified to MIL-PRF-23377 and polyurethane topcoats qualified to MIL-PRF- 85285. These coating systems deteriorate over time and must be removed periodically to allow for substrate inspections and to apply fresh coatings. The current removal processes include chemical depaint, abrasive media blasting, and hand sanding. These processes are difficult to control making selective removal of different coating layers extremely difficult. As a result the coating systems are completely removed.

The USAF is implementing robotic and handheld laser depaint systems to replace the current coating removal processes for both full aircraft and off-aircraft components to reduce process times and waste generation. The robotic systems are based on either continuous wave or pulsed fiber lasers with 1070nm wavelengths while the handheld systems are pulsed Nd:YAG lasers with 1064nm wavelengths. The lasers interact with the organic component of the coating to break down the coating for removal. The continuous wave lasers remove the coatings by pyrolizing them while the pulsed lasers ablate the coatings through thermal shock resulting from the high pulse energy. Color recognition systems on the current continuous wave robotic laser system have shown the ability to distinguish between colors of topcoats and primers allowing for basic selective removal however complete removal of the primer layer requires multiple passes increasing processing times. The handheld laser systems currently do not have such capability so it is not possible to remove topcoats without damaging the primer underneath.

The USAF is seeking either additives that can be incorporated into the current topcoats and primers making make them easier to remove or additives that can be incorporated into the primers to make them more resistant to removal by the laser systems. The proposed solution should provide the same performance properties as the current coatings. The proposed additives also cannot result in coatings with higher environmental, safety or occupational health risks than the current coatings.

PHASE I: Develop additives that can be incorporated into current coatings and evaluate laser interactions with the modified coatings. Provide an initial cost/benefit analysis.

PHASE II: Further investigate replacement solution to optimize performance. Develop a test matrix to demonstrate additional test criteria for the acceptance of the proposed solution change and perform tests. Work with aerospace

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community to preform field evaluation tests on materials/components of interest to evaluate system in “real word” environment. Update cost/benefit analysis. The use of the technology is geared specifically to facilitate stripping or non-stripping of AF coating systems. The additives will have to work with a particular type of laser that is already in use in AF depot facilities.

PHASE III DUAL USE APPLICATIONS: Work with one or more aerospace depots to demonstrate the use of the proposed solution change and explore implementation and qualification on the repair line.

REFERENCES:1. Executive Order 13423 of January 24, 2007 “Strengthening Federal Environmental, Energy, and Transportation Management.” March 19, 2015 - EO 13423 has been revoked with the publication of the new EO, "Planning for Federal Sustainability in the Next Decade." As guidance and instructions are issued for the new EO, a new EO 13693 Program Area is being built.

2. Memorandum (DTM) 12-003 “Control and Management of Surface Accumulations from Lead, Hexavalent Chromium, and Cadmium Operations.”

KEYWORDS: aerospace coatings, coating removal, lasers, paint removal

AF171-093 TITLE: Low Hyrdrogen Embrittlement (LHE) Brush Plating Chemistries for Cadmium (Cd) Replacement

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Incentivize small business to develop solutions that can replace the current cadmium (Cd) chemistries used on high strength steel aircraft components for corrosion protection.

DESCRIPTION: Cadmium (Cd) has been widely used in the aerospace industry and the Department of Defense (DoD) due to its excellent corrosion resistance, adhesion, and lubricity characteristics. Cd is a carcinogen, with heavily regulated use. DoD, Air Force, and the Occupational Safety and Health Administration (OSHA) policies require the AF to eliminate Cd uses and exposures. OSHA has issued multiple citations against AF depots with respect to Cd use. Executive Order 13423 of January 24, 2007 “Strengthening Federal Environmental, Energy, and Transportation Management” requires government agencies to reduce use and dispose of toxic and hazardous materials, including Cd. The Under Secretary of Defense Directive-Type Memorandum (DTM) 12-003 “Control and Management of Surface Accumulations from Lead, Hexavalent Chromium, and Cadmium Operations” directs the DoD to employ procedures to minimize accumulations of hazardous chemicals - lead, chromium, and cadmium.

The USAF is seeking alternative brush plating chemistries to replace the current Cd solutions used on high strength steel aircraft components such as landing gear and engine mounts. The proposed solution should provide the same, or enhanced corrosion resistance, adhesion, and lubricity characteristics while being considered environmentally friendly and reducing worker occupational health hazards. The proposed solution should not introduce hydrogen embrittlement into the components. Also, the proposed solution should not use any chemicals/compounds currently on the Office of the Secretary of Defense's (OSD's) Emerging Contaminants Watch and/or Action lists.

PHASE I: Develop a chemistry and solution that can be tested on coupons similar to AF application materials. Demonstrate preliminary evaluation criteria for application process, corrosion resistance, adhesion properties and absence of hydrogen embrittlement on limited sample size. Provide an initial cost/benefit analysis. The contractor will provide all necessary equipment and materials to perform this Phase I effort.

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PHASE II: Further investigate replacement solution optimize performance. Develop a test matrix to demonstrate additional test criteria for the acceptance of the proposed solution change and perform tests. Work with aerospace community and Air Force representatives to identify and obtain test parts from aircraft to perform field evaluation tests on materials/components of interest in “real world” environment. Update cost/benefit analysis.

PHASE III DUAL USE APPLICATIONS: Finalize test matrix to demonstrate with additional test criteria for acceptance of proposed solution change. Work with aerospace community and the Air Force representatives to perform field evaluation tests on complete system/aircraft/platform using materials/components of interest and developed in the prior Phases to demonstrate and evaluate system in “real word” environment. Update cost/benefit analysis.

REFERENCES:1. Executive Order 13423 of January 24, 2007 “Strengthening Federal Environmental, Energy, and Transportation Management.”

2. Memorandum (DTM) 12-003 “Control and Management of Surface Accumulations from Lead, Hexavalent Chromium, and Cadmium Operations.”

KEYWORDS: cadmium (Cd) elimination, environmentally benign, green chemistry, low hydrogen embrittling brush plating, worker safety

AF171-094 TITLE: Improved Non-Damaging Method of Removing Powder Coating System

TECHNOLOGY AREA(S): Materials/Processes

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop materials and processes to remove powder coatings from military weapon systems and associated equipment.

DESCRIPTION: DOD has been positioning strategically to develop new environmentally friendly anti-corrosion materials and processes. One of which is the development and usage of powder coating systems. These new coating systems are very difficult to remove with current state-of-the-art removal processes during maintenance. Millions of dollars are spent every year in repair/refurbish or condemning actions on aerospace weapon system components that have been de-painted using current technologies to remove the new coating systems. The current state-of-the-art process to remove these types of coatings usually involved chemical or a dry media removal. These coatings tend to be difficult to remove and current methods have hazardous waste issues.

The purpose of this effort is to develop methods to remove powder coating systems from the multiple substrates, especially soft substrates like magnesium on aerospace housings and other aerospace components. Various methods, such as (chemical, mechanical media in water and/or water blasting, or laser and flash jet removal technologies), need to be explored during this effort. Use of any government materials, equipment, data, or facilities will not be required for this effort since the proposed technology could be applicable to many powder coating refurbishing

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operations, both DoD and non DoD. The project will provide the government and industry with a non-damaging method of powder coating removal and not cause severe damage during the removal process. The result will be fewer condemned components due to substrate removal/damage during the coating removal process.

Additional objectives are as follows: (1) The process shall be non-toxic and environmental friendly, (2) it shall be easy to preform and be field-level implementable (using current utilities), and (3) when coating system is removed the surface profile should be without any defects and ready for a new coating system application. (Surface profile would be similar to a near white metal condition typified by the Near White Metal, SSPC-SP 10, NACE #2 for Steel.), (4) with no (objective) or minimal (threshold) new training and personal protection equipment to accomplish the difficult powder coating removal process.

PHASE I: Develop formulations and processes to remove the powder coating from metal and/or composites. These formulations and processes would also need to demonstrate no damage to the substrates. Develop a return on investment estimate and update it as the project progresses.

PHASE II: Advance the Phase I formulations and processes to improve the powder coating removal consistent with MIL-PRF-24712 performance specifications. Demonstrate that these materials and processes can be used as a drop-in replacement for current coating removal processes being used. Develop a draft specification.

PHASE III DUAL USE APPLICATIONS: Military Application: Evaluate selected formulation and processes vs. currently approved coating removal methods per T.O. 1-1-8. Perform coating removal testing and verify powder coating removal capability; revise formulation as necessary.

REFERENCES:1. T.O. 1-1-8, Application and Removal of Organic Coatings, Aerospace and Non-Aerospace Equipment.

2. T.O. 35-1-3, Corrosion Prevention and Control, Cleaning, Painting, and Marking of USAF Support Equipment (SE).

KEYWORDS: blast media, cleaning, materials, mechanical removal equipment, nano-materials, powder coatings

AF171-095 TITLE: Computational corrosion modeling for Condition Based Maintenance Plus (CBM+)/aircraft environment tracking

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop a corrosion model which tracks aircraft environmental exposure using off-board sensors and produces a corrosion severity index which can be used to adjust the corrosion related maintenance activities based upon the condition of the aircraft.

DESCRIPTION: The USAF expends a large amount of resources on corrosion related maintenance and is seeking ways to reduce the resource burden with little to no impact on performance. One potential area for improvement is aircraft wash frequency. Current USAF wash intervals are dictated by TO 35-1-3 (support equipment) and TO 1-1-691 (aircraft). The technical orders correlate wash intervals with the environmental severity of the assigned location of the asset. Aircraft assigned to a specific geographic location do not exclusively operate in that location. Operational mission assignments frequently drive aircraft away from their assigned location and potentially into a different environment. Differences in aircraft usage can also drive different rates of corrosion. Not all aircraft assigned to the same base see the same usage. Some aircraft will experience a higher operational tempo than others. The current technical orders do not take into account asset usage when determining wash intervals. Additionally, support equipment environments can change based upon asset storage conditions. Some equipment may be stored

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indoors while other equipment is stored primarily outdoors. Another concern is the fact that environmental conditions are not constant and vary over time. The environmental severity categories that are included in the technical orders are based on a long term measurement of the environment at the location. This static approach does not take into account transient changes in the weather which could have a large impact on the environmental severity at any given location.

The USAF seeks to develop a corrosion model which incorporates asset environmental exposure (duration, location, season, weather, pollutants) as inputs to produce a cumulative corrosion severity or damage metric. The environment can be characterized using off-board sensors or other available data (weather, atmospheric, etc.) from reputable sources. The actual location of assets can also be determined from current USAF data systems. The fusion of actual environment and location data can yield an asset level corrosion severity index. The cumulative corrosion damage metric would be used to adjust equipment wash intervals based upon the specific condition of the equipment which would be a result of the actual environmental conditions the equipment has been exposed to. The potential exists to expand the scope of this methodology beyond wash intervals and eventually control all scheduled corrosion related maintenance activities based on of the asset level corrosion severity index. An ideal model framework will have sound scientific underpinnings based on materials behavior, be extensible in follow on efforts to include additional factors that might arise in specific situations (or be omitted if not relevant to a particular application), and support a path to implementation including integration with available resources and assets. Time-independent methods that do not consider environmental fluctuations are not of interest in this solicitation.

PHASE I: Identify critical environmental and asset usage factors contributing to corrosion. Develop model to predict a cumulative corrosion severity based on exposure and asset usage inputs. Quantitative measurements of corrosion selected by the contractor shall have a correlation coefficient (R-squared) between predicted and observed results of at least 0.75 in previously demonstrated applications to be considered competitive. Select COTS sensor suite to monitor identified off-board environmental parameters as well as on- board sensors to support model validation.

PHASE II: Develop plan for adjusting aircraft wash and inspections based upon model outputs. Demonstrate correlation of observed and predicted corrosion results on models developed in Phase 1 for at least a one year time period. Develop aircraft tracking application to use all available LIMS-EV data as an input and produce an accurate history of aircraft location. Integrate aircraft location data into corrosion severity index model. Procure and install off-board environmental sensor package at selected pilot locations.

PHASE III DUAL USE APPLICATIONS: Implement & use corrosion severity index model on B-1 & C-5 systems to determine aircraft wash intervals & other field level corrosion related inspections. Validate model using small group of B-1 & C-5 aircraft and related support equipment and ensure the model correlates with on-board measurements.

REFERENCES:1. Abbott, W. H., Pate, Henry O., and Fernandez, Felix, “Acceleration Factors for Severe Outdoor Exposures vs. Flight on Military Aircraft,” available atwww.corrdefense.org.

2. Morefield, S., Drozdz, S.A., Hock, V.F., Abbott, W.H., Paul, D., and Jackson, J.L., “Development of a Predictive Corrosion Model Using Locality-Specific Corrosion Indices”, final report, ERDC/CERL TR-09-22, August 2009.

3. Rose, D.H.,"A Cumulative Damage Approach to Modeling Atmospheric Corrosion of Steel”, Ph.D. dissertation, University of Dayton, 2014.

4. Summitt, R. and Fink, F.T., “PACER LIME: An Environmental Corrosion Severity Classification System”, AFWAL-TR-80-4102 Part 1, August 1980.

5. Summitt, R. and Fink, F.T., “PACER LIME: Part II – Experimental Determination of Environmental Corrosion Severity”, AFWAL- TR-80-4102 Part 1, June 1980.

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KEYWORDS: aircraft environmental exposure, aircraft wash intervals, corrosion, corrosion model, corrosion severity index, predictive, CBM+, model

AF171-096 TITLE: Improved Casting Quality through Novel Engineered Ceramic Molten Metal Filters Improved Casting Quality through Additively Manufactured Ceramic Molten Metal Filters

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Incentivize small businesses to utilize advances in ceramic manufacturing, including, but not limited to, additive manufacturing, to develop new and/or improved ceramic filters used in metal casting processes leading to significantly cleaner and less porous castings

DESCRIPTION: Aerospace and commercial metal casters utilize ceramic filters to insure clean uncontaminated metal flows into the mold. One of the most common filters is made from reticulated ceramic foam. Current ceramic foam filter designs produce significant variation in metal flow rate and do not always remove 100% of contaminants. A published study (1) of foam filters found a significant variation in filtration efficiency. For a single, typically used grade (i.e., pore size) of ceramic foam filter the average filtration efficiency was only 69%. More concerning, the piece-to-piece measured filtration efficiency varied between 21 and 93%. In another published study (2), the authors evaluated the physical structure of reticulated ceramic foam filters from the four largest filter manufacturers. For this same typically used filter grade, the supplier-to-supplier variation in pore diameters for filters with an average filter pore diameter of 2126 microns was 578 microns. In a further study of filter efficiency (3) the authors found, as expected, that when the incoming metal was relatively clean (i.e., low levels of small inclusions), improved filtration occurred using finer filter grades, but they also noted individual filter performance was significantly influenced by variations in the physical properties of the filter. Finer filter grades require increased metal priming height and can easily clog leading to disruptions in metal flow and undesirable casting porosity. In critical aerospace applications where a tree of parts is simultaneously cast with a filter in each individual cavity, filter-to-filter differences in permeability can result in unpredictable differences in individual cavity fill times. The better solution would be to develop a more consistent ceramic filter. What is required is a range of filter sizes consistent with current commercial filter grades 30 through 80 that show permeability repeatability within 5% filter-to-filter.

Ceramic filters used in metal casting must meet a number of requirements. They must be mechanically strong enough to survive assembly into the mold and metal pouring, and they must be chemically resistant to molten metals and thermally shock resistant to the mold burn out and casting process. Efficient filters must have a large surface area and act as a getter material that can attract and retain nonmetallic inclusions and contaminants. Most important, they must have a predictable porosity that produces a consistent and controllable permeability. For current ceramic foam filters meeting the latter requirement is the most challenging as the filters are produced from a highly-random, reticulated polymeric foam precursor infiltrated with ceramic slurry. Thus, ceramic foam filters are sold based upon pore density (pores/inch) and not permeability.

Advances in ceramic manufacturing, including additive manufacturing techniques, have made it possible to produce very repeatable parts with highly engineered internal structures. The USAF is looking to improve metal casting processes through the use of improved manufacturing to develop and demonstrate step change improvements in ceramic molten metal filter design and manufacturing.

PHASE I: Develop prototype filter designs and produce sample filters. Flow test prototypes demonstrating a range of filter permeability consistent with current commercial foam filter grades 30 through 80. Demonstrate filter-to-filter statistical repeatability of permeability. Should complete at least one metal pour demonstrating filter survivability. Provide an initial cost/benefit analysis.

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PHASE II: Further investigate filter designs to optimize performance. Work with aerospace caster producing typical aerospace alloy pours. Demonstrate multiple, engineered filter designs resulting in robust mechanical properties, predictable metal flow rate, and statistical significant improvement in casting cleanliness/porosity with no deleterious casting impact. Key process parameters understood with demonstrated capability to produce prototypes in manufacturing relevant environment. Update cost/benefit analysis.

PHASE III DUAL USE APPLICATIONS: Work with one or more aerospace casters demonstrating use of designed filters on a range of critical investment castings supplied for use on the latest generation fighters and tankers. Work with industrial metal casters to explore implementation and qualification on select commercial applications.

REFERENCES:1. N. J. Keegan, W. Schneider, H. P. Krug, “Efficiency and Performance of Industrial Filtration Systems”, 6th Australasian Pacific Course and Conference, Aluminum Casthouse Technology: Theory and Practice (ED: M Nilmani, TMS 1999, pp 159 -174.

2. Steven F. Ray, “Recent Improvements in the Measurement and Control of Ceramic Foam Filter Quality”, Presented at the International Melt Quality Workshop, Madrid, Spain, 25-26 October 2001.

3. N. J. Keegan, W. Schneider, H. P. Krug, “Evaluation of the Efficiency of Fine Pore Ceramic Foam”, Light Metals 1999, pp 1031 – 1041.

KEYWORDS: additive, casting, ceramic, filters, manufacturing, metal

AF171-097 TITLE: High temperature moisture sealants for hot exhuast structures on advanced system

TECHNOLOGY AREA(S): Materials/Processes

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop and demonstrate a high temperature moisture sealant to go over the ceramic coatings on existing turbine engine exhaust system ceramic of the advanced fleet. The coating and its application methods should be suitable for production, depot, and field repair.

DESCRIPTION: High temperature exhaust coatings are used for improved survivability in a variety of advanced aircraft engine exhaust applications, but they often have limited durability due to moisture effects. Their importance for aircraft safety and warfighter dominance cannot be understated. By weight, these coatings on advanced aircraft correspond to < 1 %, but they are often in the top 3 maintenance drivers on an annual basis with extensive downtimes and inspection protocols, not to mention severely limiting logistics and planning. These coatings are typically somewhat porous, often being air plasma sprayed or electron beam deposited, and may have spalling issues due to moisture exposure and reaction (causing cohesion failures at 25% of their design life).

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The goal of this effort is to identify and optimize a high temperature sealant chemistry that could be applied over the existing exhaust coating without causing knockdowns in coating performance but provide better life due to moisture resistance. Some studied sealant systems are provided in the references. The application method and cure method for these sealants will be important because only the exterior of the exhaust panel needs to be sealed and not the panel sides or back face. So characterization of the sealant thickness, its uniformity and ability to be applied to a single side of an exhaust panel will be important and will need to be assured via SEM and possible TEM analysis. The offerer will also need to demonstrate the benefit of the high temperature sealant against repeated moisture exposures via a series of thermal, mechanical, and electrical tests (these tests are usually defined by the prime engine manufactures). For example it has been shown in the past by four point bend test and cantilever bend test that when the coated exhaust panels are exposed to 10 wet/dry cycles (16 hr soak followed by 150°F dry) that their modulus is increased by 2X and their strain to failure decreased by 2X resulting in a cohesive coating failure. Additionally, a coated, sealed and exposed panel then needs to pass a temperature durability test via cyclic burner rig testing (usually 2000 to 4000 cycles at 1800°F). Finally the panels will need to go to an environmental burner rig testing which combines both moisture exposure and burn rig testing sequentially until failure occurs. The electrical testing needs to be defined and conducted by an engine prime contractor. It is also important to remember that another focus of this effort is on a simple application method that could be employed at the part manufacturing facility, at repair depots and also in the field on large components. Teaming with an engine OEM is highly recommended for insight into coating characteristics, operating conditions, and performance requirements.

PHASE I: Explore sealant chemistry, application methods, and heat treatment cure requirements. Demonstrate feasibility of the sealant via limited characterization using bend testing screening methods on coated, sealed, and moisture exposed substrates purchased from an OEM or their coating vendor. No government equipment or supplies will be available to the program.

PHASE II: Optimize sealant chemistry, application method, and heat treatment to assure uniform coverage without pore close-off which increases to modulus. Have the sealant applied at the OEM facility on their proprietary materials. Have the OEM conduct cyclic burner rig testing, environmental burner rig testing and electrical testing on the coupons.

PHASE III DUAL USE APPLICATIONS: Contractor complete qualification testing and transition the technology to an engine OEM end user and/or maintenance depot.

REFERENCES:1. "Protective Coatings and Thin Films" by Y. Pauleau and P.B. Burma @https://books.google.com/books id=ApTI7h7Db2UC&printsec=frontcover#v=onepage&q&f=false

2. "Engineering Materials Handbook : Adhesives and Sealants" by ASM International Handbook Committee 1990 @https://books.google.com/books?id=kb0RAQAAMAAJ&q=Thin+film+moisture+resistant+sealants+for+high+temperature+ceramic+coatings&dq=Thin+film+moisture+resistant+sealants+for+high+temperature+ceramic+coatings&hl=en&sa=X&ved=0ahUKEwiY nY3Q0ZDMAhXJOyYKHfX2DfoQ6AEINTAA

KEYWORDS: coatings, engine, exhaust, high temperature, moisture, sealant

AF171-098 TITLE: Quantification of microtexture regions in titanium alloys using optical sensing methods

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop optical-based experimental methods that can rapidly and cost-effectively characterize the size and the anisotropic crystal orientation of the alpha-phase for titanium alloys, for features 0.05 millimeters in

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scale and larger.

DESCRIPTION: While metallic forgings are often considered to be relatively homogeneous, they can contain significant variations in the internal microstructure that result from variability in upstream processing. Titanium alloys, for example, are prone to the development of “microtexture regions,” (MTR) wherein clusters of grains with similar crystallographic orientation persist over millimeter and larger length scales [1]. These microtexture regions can significantly impact the fatigue crack growth rate, especially under loading conditions containing tensile dwell periods.

One state-of-the-art method to accurately size and detect the presence of such features at the surface of metallic laboratory samples is Electron Backscatter Diffraction (EBSD) analysis using a Scanning Electron Microscope (SEM) [2]. While this method provides high spatial resolution data, it is a relatively slow process with typical data acquisition rates less than 1.5 kHz per data point, requires the sample to be placed within the SEM vacuum chamber with constraints over sample size and volume, and the sample surface must be nearly damage-free which can be laborious to prepare.

This solicitation is focused on the development of novel technologies that offer significant improvements relative to the state-of-the-art to rapidly detect and size both grains and MTR features in Titanium alloys. Of specific interest are optical-based experimental methods that are capable of quantifying the size and the anisotropic crystal orientation of the alpha-phase for titanium alloys, for features such as grains and MTR that are 0.05 millimeters in scale and larger, for sample areas in excess of 75 x 75 mm. It is critical that such techniques significantly reduce both the time and surface quality requirements compared to EBSD-based analysis. Other desired outcomes are that the characterization can be performed in air without the need for specialized environmental control, leveraging commercial-off-the-shelf technology if possible.

It is anticipated that rapid and accurate quantification of MTR in laboratory samples will allow for improved component design and lifting methodologies for systems that utilize titanium alloys, and, may also enable improvements in non-destructive inspection capabilities via correlative analysis and quantification of laboratory samples containing MTR. In addition, demonstration of the applicability of such technology to other aerospace or structural engineering alloy systems that contain phases with anisotropic optical properties, such as Titanium Aluminides, Beryillum, Magnesium, and Zirconium alloys is also desired.

PHASE I: Clearly define the system concept for the optical characterization system, which includes a detailed description of system capabilities, addressing both known and anticipated issues with system development and the technical approach to mitigate said issues, and estimates system cost.

PHASE II: Build a prototype using the design developed from Phase I. Demonstrate system performance on representative structural titanium alloys that contain selected grains and microtexture regions larger than 0.05 mm in scale, for sample areas in excess of 75 x 75 mm.

PHASE III DUAL USE APPLICATIONS: Grain and MTR quantification systems have the potential for use both at DoD facilities, as well as by original equipment manufacturers and the industrial materials supply base, which rely on microstructural characterization to fabricate, develop, and utilize alloys prone to MTR development.

REFERENCES:1. N. Gey, P. Boucher, E. Uta, L. Germain, M. Humbert, “Texture and microtexture variations in a near-a titanium forged disk of bimodal microstructure,” Acta Materialia 60 (2012) 2647–2655.

2. Electron Backscatter Diffraction in Materials Science, Editors: Schwartz, A.J., Kumar, M., Adams, B.L., Field, D.P., (2009) Springer-Verlag,    DOI10.1007/978-0-387-88136-2.

KEYWORDS: characterization, microtexture, microtexture region (MTR), MTR, optical, optical characterization, titanium, titanium alloys

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AF171-099 TITLE: Diffusely Scattering Paints for Remotely Piloted Aircraft

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop sprayable paint system highly efficient (threshold 95% objective >98%) at reflecting or backscattering visible or shortwave infrared light for thermal control.

DESCRIPTION: Remotely piloted aircraft are deployed early and often to perform unusual or unique mission sets. Emerging operational needs may require sprayable coatings that achieve high visible (VIS) and short-wave infrared (SWIR) light rejection (i.e., via reflection or backscattering) to achieve precise thermal control. The objective of this topic is to develop specialty coatings for remotely piloted aircraft that are lightweight, serviceable, and highly efficient at reflecting/backscattering Vis/SWIR light. Relevant reviews of the scientific literature are given in the references section.

The custom coatings developed in this program should be compatible with existing coating deposition methods, such as pneumatic high volume low pressure sprayers and ambient temperature curing. Coatings should achieve a total (diffuse and specular) reflectivity of 95% (threshold) >98% (objective) across as broad a spectral range as possible, specifically including Vis and SWIR spectral regions. Beyond processing requirements, the coatings must be robust, providing corrosion protection, mechanical durability, UV stability, thermal stability, and other properties typical of high performance aerospace grade paint formulations. It is anticipated that existing commercial primer systems will suffice in attaining the desired optical properties and not require redevelopment; however if the offeror thinks that primer development is necessary, then it should be proposed. While a variety of molecular structures are tenable for processing and durability requirements, the structure should be designed and selected to minimize direct absorption of the light by the polymer. As such, the anticipated solutions are polyurethanes, polysulfides, and epoxy based polymers; however other molecular structures may prove successful in attaining the given performance. It is anticipated that the offerors will employ an existing binder system and develop a novel formulation of fillers to achieve the necessary total reflectance values. Offerors are encouraged to reduce or eliminate hazardous VOCs, hexavalent chromium, and strontium chromate from any formulations.

Generally, the goal is to develop a coating in compliance with MIL-PRF-32239 (available at http://quicksearch.dla.mil/), with the exception of those elements of the specification relating to maximum infrared reflectance. The coating developed need not achieve every performance metric at the outset, but over the course of all three phases of the program coatings are expected to be capable of the performance metrics outlined in the specification.

No government facilities are anticipated in the performance of this effort. Offerors are encouraged to source their own metallic and graphite composite substrate coupons representative of high performance aerospace structures; though government assistance in procuring such coupons may be proposed. It is encouraged that the offeror anticipate necessary quality control metrics and plan for the ability to execute reflectivity measurements quickly and economically during the course of the program.

PHASE I: Formulate coating, apply to test coupons, measure and maximize total reflectance values. Create and deliver raw material sample (>= 1 liter) capable of being spray deposited. Deliver residual test coupons to government. Assess and document processability of the material, including identifying preliminary quality metrics and process controls.

PHASE II: Further refine formulation to maximize total reflectance. Assess and document durability of the material, including thermal exposure, UV exposure, solvent compatibility, and mechanical durability. Deliver (>= 10 liters) of material for assessment by AF representatives. Assess and document processing windows, deposition parameters, adhesion, and metrics for quality assurance. Deliver residual test coupons to government.

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PHASE III DUAL USE APPLICATIONS: Further advance manufacturing maturity and production capacity. Finalize understanding of adhesion, compatibility, durability, aging, and quality control. Commercial applications include energy efficient solar paints and thermal control applications. Military applications include the AFLCMC platforms, including WI.

REFERENCES:1. Philips-Invernizzi B, Dupont DE, Caza´ CA, Bibliographical review for reflectance of diffusing media, Optical Engineering, 2001, 40 (6):1082-92.

2. Kinoshita, S. & Yoshida, A, "Investigating performance prediction and optimization of spectral solar reflectance of cool painted layers," Energy and Buildings, 2016, 114:214-220.

3. S. Wijewardane, D.Y. Goswami, “A review on surface control of thermal radiation by paints and coatings for new energy applications,” Renewable and Sustainable Energy Reviews, 2012, 16(4):1863-73.

4. Raman, A.P., Anoma, M.A., Zhu, L., Rephaeli, E., Fan, S., "Passive radiative cooling below ambient air temperature under direct sunlight", Nature, 2014, 515:540.

KEYWORDS: backscattering, diffuse reflectance, high volume low pressure spray, paint, polymer, polysulfide, polyurethane, thermal control

AF171-100 TITLE: Manufacturing and Metrology of High Magnetic Permeability Materials for High Efficiency, Wideband, and Conformal RF Antennas

TECHNOLOGY AREA(S): Materials/Processes

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Mature material synthesis and metrology for high-permeability materials to enable magnetic high-impedance ground planes. Mate materials with models to predict RF antenna. Demonstrate broadband (HF to UHF), efficient, conformal RF antenna.

DESCRIPTION: RF signal collection and wireless communications across many different frequency regimes require underlying antenna technology that is capable of operating over extremely broad frequency ranges, typically from HF (~2 MHz), to UHF (~3 GHz), often with the added desire to have such an antenna be conformal for a host of reasons, including non-protruding surfaces and reduced drag.

Traditional electronic circuits and radiating elements (aka antennas) face significant challenges in providing high radiation efficiency across this wide bandwidth, let alone in also attempting to meet compact and conformal platform requirements. Indeed, for an antenna with a longest dimension that fits within a sphere of radius a, the Efficiency Bandwidth Product (EBWP)[1] cannot exceed EBWP = 1/Q_rad ~ (2*Pi*a/lambda)^3. Here, Q_rad is the ratio of the reactive energy stored in the near field of the antenna per cycle to the power radiated to the far field

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by the antenna. Further, for antennas restricted to a surface mount—as is typically the case when employing an electrical antenna against a metal ground plane to meet a conformal requirement—this limit is further reduced by a factor of 4. A second challenge facing broadband antennas occurs for electrical circuit antenna designs implemented against low (electrical) impedance environments. Whether mounting such to sides of cars, against walls, or integrated onto an airframe, the electrical currents induced by such a conformal metal antenna result in image currents that oppose the radiating current. As the far field radiated power by such an antenna carrying a current I is given by P_rad=(I)^2 * R_rad/2, the decrease in radiation resistance from such opposing currents further drops the EBWP by the same factor. Hence, conventional electrical circuits mounted to dielectric/metal ground planes force severe choices between achieving conformal design, large bandwidth of operation, and radiating efficiency.

Recently, new conformal antenna designs have been demonstrated utilizing magnetic circuits [2, 3]. In these experiments, high magnetic impedance substrates, such as NiZn (a traditional anechoic chamber tile material for RF damping), Permalloy, and similar high µ materials, have actually comprised both the ground plane and antenna for broadband, efficient, and conformal antenna demonstrations. These experimental realizations have also shown that the proper selection complex permeability, µ(f) = µ’(f)-jµ”(f), comprising the ground plane plays a key role in RF performance. Larger loss (µ”) is actually shown to improve antenna bandwidth, counter to conventional electrical circuit designs, whereas the magneto-dielectric antenna radiation efficiency is related to the so-called “hesitivity,” [2,3], measured in Ohm/m, which is the peak of the magnetic conductivity spectrum for various magnetic material families. Stated more succinctly, high hesitivity materials where µ”>>µ' (that is, in a traditionally large loss regime) over the targeted frequency band of operation offer a new design paradigm for the most efficient broadband magnetic-circuit antenna.

To make such new antenna designs ubiquitous for DoD applications, improved manufacturing and metrology techniques are required. This includes either new material creation or manufacturing improvements of traditional materials [4]. The two fundamental classes of such materials are ferrimagnetic ceramics (ferrites) and ferromagnetic metals. Challenges for both classes exist in terms of maintaining an effectively high permeability (hesitivity) while creating large area films, laminates, or moldable sheets that also resist degradation due to humidity, corrosion, UV exposure, temperature swings, or similar environmental exposure.

PHASE I: Identify best candidate magnetic film material for synthesis maturation to enable broadband and conformal magnetic-circuit-based antenna demonstration. Produce sample quantities, and verify the sample quality both through material/sample level metrology as well as RF antenna demonstration. Ideally, target such demos across the entire 2 MHz - 3 GHz range, and compare performance to conventional surface-mount antenna designs.

PHASE II: Demonstrate large-area (> 1 m**2), high-tolerance moldable sheets or films of magnetic materials and fabrication metrology. Demonstrate material performance across multiple RF bands via magnetic circuit implementation. Compare performance to both models as well as existing surface-mount antennas. Establish material metrics, validated against antenna demonstration. Project frequency and efficiency metric limits across RF spectrum based upon path to further synthesis and fabrication maturation.

PHASE III DUAL USE APPLICATIONS: Develop data sets for material quality, performance specifications, and expected cost and yield models. Generate samples for fielding in relevant environments (temperature, corrosion, etc.). Study material reliability of conformal antennas for RF sensing, communications, and other DoD applications.

REFERENCES:1. Smith, M.S., “Properties of dielectrically loaded antennas”, Proc. IEEE, 1977, 124, (10), pp. 837-839.

2. Sebastian, Clavijo, Diaz, Daniel and Auckland, “A new realization of an efficient broadband conformal magnetic current dipole antenna”, IEEE APS-URSI meeting 2013.

3. Diaz, Daniel and Auckland, “A new type of conformal antenna using magnetic flux channels MILCOM Oct 6-8 2014, Baltimore MD.

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4. Venkatasetty, Electrodeposition of thin magnetic permalloy films, J. Electrochem. Soc., Vol. 117, No. 3 March 1970, pp. 403- 407.

KEYWORDS: broadband antennas, conformal antennas, high permeability composites, high permeability materials, high permeability thin films, magnetic circuits

AF171-101 TITLE: Additive Manufacturing of Freeform Optical Elements for Imaging System Weight and Volume Reduction

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Demonstrate the utility (cost, schedule, and performance) of additive manufacturing for large (= 250 mm diameter) freeform optical elements operating in reflection and transmission. Demonstrate weight and volume reductions over current systems.

DESCRIPTION: The field of freeform optics is growing significantly yearly [1] and shows tremendous promise in reducing the mass and volume of attendant optical imaging systems operating at nearly any wavelength. Indeed, such mass and volume reduction can ultimately increase lifecycle sustainability of military electro-optic and infrared (EO/IR) imaging systems by allowing more cooling or other electronics. Further, freeform optical designs may provide for a thermalization of key elements, reduced imaging system integration and assembly costs, and potential for reduced aberrations in imaging over very wide optical bandwidths. Commercially, the field of freeform optics is also receiving attention in reduced size and higher performance mobile imaging applications (cell phones and portable, lightweight cameras), in cinema (both filming and projecting), and in entertainment and gaming (lightweight and rugged virtual reality goggles, for example).

In like fashion, the techniques of additive manufacturing (AM), such as material jetting (including inkjet printing, electro-hydrodynamic jetting, and others), material extrusion, powder bed fusion, and direct energy deposition, among others, are creating an international flurry of interest and burgeoning capability to produce objects not achievable by traditional “subtractive” manufacturing methods [2]. Further, AM offers unique acquisition advantages to military systems that are notoriously small in quantity but high in performance and complexity of integration.

The mating of these two techniques—freeform optics for high-performance, low-mass/low spatial volume, aberration-free imaging systems—and AM for rapid, flexible, and high-performance low-volume-rate production—offer unique capability for emergent imaging concepts and demonstrations. The goal of this topic is for the proposer to demonstrate AM of a large aperture (>=250 mm in diameter) freeform optical imaging system—one transmissive, one reflective. Special attention and consideration will be given to (1) utilizing processes and materials for demonstrations in military relevant wavelength bands, namely short-wave infrared (SWIR, 1.4 µm to 3 µm ), mid-wave infrared (MWIR, 3 µm to 5 µm), and long-wave infrared (LWIR, 8 µm to 14 µm); (2) demos providing imaging system demonstration spanning larger portions of these wavelength bands; (3) proposals developing processes using materials known for favorable environmental robustness (e.g. athermal imaging system designs, materials that are not susceptible to damage from high power incident electromagnetic radiation, and radiation hard and shock and vibration robust materials and processes). Relevant demonstrations may include telescope systems, heads-up display systems, extremely wide-field of view (WFOV) optics, novel and highly accurate beam-steering systems, robust low-light level imaging (for example, hyperspectral imaging with reduced optical scatter), among others.

PHASE I: Identify candidate materials and additive manufacturing (AM) processes to demonstrate military relevant freeform optical imaging elements. Use AM to create and verify the performance of a small-scale (diameter >30 mm) transmitting OR reflecting freeform element. Compare performance to commercial element performing same

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function. Assess AM production trade-offs (cost, schedule).

PHASE II: Demonstrate large-scale (>= 250 mm diameter) reflective and transmissive freeform optical imaging systems via AM, assess cost, schedule, and performance of low-volume manufacture. Assess imaging quality and ruggedness of such elements, including varying ambient temperature (-50 C)

PHASE III DUAL USE APPLICATIONS: Optimize materials and AM processes to demonstrate freeform elements across wide swaths of SWIR, MWIR, and LWIR bands. Conceive and demonstrate in-line metrology for reduced schedule of manufacture. Project manufacturing costs and schedule for low-rate to larger volume manufacturing runs.

REFERENCES:1. Rolland, J. and Thompson, K., “Freeform Optics: Evolution? No, revolution!” on the 19 July 2012 SPIE Newsroom (DOI: 10.1117/2.1201207.004309, accessible viahttp://spie.org/newsroom/4309-freeform-optics-evolution-no-revolution? ArticleID=x88361).

2. Diegel, O. et al., “Tools for Sustainable Product Design: Additive Manufacturing,” J. of Sustainable Development, Vol. 3, No. 3, September 2010, pp. 68-75.

KEYWORDS: additive manufacturing (AM), AM, athermal imaging system designs, beam-steering systems, extremely wide field of view (WFOV) optics, WFOV optics, freeform optical imaging, freeform optics, heads-up display systems, hyperspectral imaging, low-light level i

AF171-102 TITLE: Portable, Precision Automated Welding for Aerospace Alloys

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop a portable, automated weld system capable of being taken to a work area to perform automated precision weld repairs on aerospace grade materials.

DESCRIPTION: Performance of structural maintenance and repair on aircraft requires precision welding of advanced aerospace alloys such as Ti 6-4, Ti 6-2-4-2 Si, Al 7075, and Al 6061 on thicknesses up to .25" and lengths up to 6”. Air Force desires a portable automated welding system that can be transported to a work area using normal ground support equipment.

The system must be capable of automatically identifying manually prepared weld location and required weld length and size when queued with rough location data. The data must flow into automated instructions for weldment path and proper weld penetration. Post weld automated inspection must be performed to visual requirements of MIL-STD-2219A Class A to identify completed weld size, shape, and defects. All weld data including post weld inspection, weld settings, process monitoring, and final weld profiles must be captured and stored for use in digital thread. Temperature control of weld and surrounding area required.

Current state-of-the-art (SOA) in the Air Force is manual weld inspection, manual repair and weld preparation, and manual weld and manual weld surface finish. In response to lack of skilled labor and desire for repeatability and precision welding, there is need at depot for automation of some or all of these processes. Industry SOA is weld environment appropriate vision and laser seam finding systems capable of creating 3-D weld profiles of prepped weld joints and automated weld inspection systems capable to detect weld defects down to .005”. Other research programs are addressing the automated NDE and pre weld joint prep and post weld grinding. System flexibility for future capability insertion for automation would include damage NDE, weld prep, post weld finishing and post weld NDE inspection. Current state for automation is increased productivity and repeatability. This program proposes precision welding including penetration and temperature control, integration of vision or laser systems to identify

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weld joint location, shape and completed weld profiles, and flexibility from automation.

PHASE I: Perform trade studies and research to identify appropriate automation for motion control, precision welding process including penetration control and temperature sensing/control, preweld location and joint configuration mapping and post weld visual inspection scheme, weld monitoring scheme and appropriate sensors, location queuing process, software and hardware requirements including development of graphical user interface (GUI) for operator inputs and system outputs and input requirements for new materials. Identify process to develop location specific weld schedules and parameters necessary to monitor for location specific weld schedule. From results of trade studies and research, provide report identifying preliminary automated weld cell concept and development required to achieve system identified in description.

PHASE II: Design and develop an automated system capable of delivering precision welds and demonstrate on Ti 6-2-4-2 Si plate. When queued with rough location input and start command, automatic detection of weld joint size and location must produce location specific weld parameters for the specified material. Demonstrate GUI for operator inputs, system outputs and system flexibility for addition of materials and future capabilities. Demonstrate temperature control for weld and surrounding weld area. Demonstrate weld monitoring and vision inspection capability. Perform development of location specific weld schedules and demonstrate input capability and flexibility to add new material data. System must be able to control weld parameters in order to achieve precision weld penetration, weld integrity and optionally control temperature limits to protect surrounding materials. From results of Phase II system development, design a portable automated weld cell. Provide analysis of cost, maintenance, and training of the equipment. Provide a list of potential components that could be repaired using this capability.

PHASE III DUAL USE APPLICATIONS: Manufacture and demonstrate a portable, automated weld system capable of precision weld repairs on aerospace grade materials. Demonstrate process of development and input of new material of interest. Demonstrate data capture for digital thread. Prepare a manufacturing plan, bill of materials (BOM0, users' manual and training plan. Develop a test and certification plan and demonstrate on Air Force Depot application of interest. Perform cost analysis and business case for Industry insertion. Perform business case for commercial application and identify key applications areas in the commercial and military markets.

REFERENCES:1. Department of Defense Standard Practice, MIL-STD-2219 Class B. Retrieved from: everyspec.com/.../download.php?spec=MIL-STD-2219A.010187.PDF.

2. Gas Tungsten Arc Welding. Retrieved from:www.itw-welding.com/media/Pdf/Welding_Support/QSTIGe.pdf.

3. Michael Francoeur, President of Joining Technologies Robotic Industries Association. Gas Tungsten Arc Welding. Retrieved from:http://www.robotics.org/content-detail.cfm/Industrial-Robotics-Industry-Insights/Gas-Tungsten-Arc-Welding/content_id/164.

4. Note: No references for robotic or automated material identification, weld inspection, weld preparation and welding. All technologies exist as individual robotic and automated processes but there is no reference to an integrated system that includes all p

KEYWORDS: gas tungsten arc welding (GTAW), GTAW, robotics, weld and inspection automation, weld inspection, weld repair

AF171-103 TITLE: Tailpipe Coating Thickness Measurement Capability

TECHNOLOGY AREA(S): Air Platform

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The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a field-level capability to inspect coating thickness in high temperature exhaust components. The technology must be applicable to complex geometry surfaces as well as over varying substrates and thermal barrier coating materials.

DESCRIPTION: Current Air Force aircraft have thick thermal barrier coatings that require precise thickness deposition along the exhaust features. To maximize the service life of the high temperature exhaust systems, the coatings are required to provide a thermal barrier and must meet minimum thickness requirements for effective protection. Over applying coatings will add weight to the aircraft and provide no additional benefit. Therefore, accurate coating thickness is critical for peak mission performance. Maintaining the thicknesses of these coatings during the service life of the exhaust is critical for performance. Currently, there is no field-level thickness measurement capability. A capability gap exists to be able to accurately and repeatedly measure and maintain the coating thickness while in service. Consequently, a need exists for a handheld, lightweight probe that provides a localized measurement of coating thickness.

Capability must be either man-portable (objective of no more than 7 lbs. and threshold of no more than 5 lbs.) or able to be attached to an autonomous delivery system. Technology must meet an threshold accuracy of +/- 20% of nominal value, or objective accuracy of +/- 10% of nominal value. Technology must scan defects up to a size of 12 in. x 12 in. in area at a resolution of .10 inches. Collection time should not exceed 1 minute. Rigorous technology demonstrations using representative targets shall be performed. To that end, correlations between current baseline systems and the new technologies shall be carried out. Specifically, an optimized hardware and software system solution to provide capability to an unsophisticated maintainer or technician (AF 5-level) that is reliable, repeatable, and easy to use. This strategy is centered on developing a robust tool with advanced algorithms and processing for production, depot- and field-maintenance crews that only require “entry level” user training and knowledge to be successfully used and operated. New equipment and technology shall meet Class1/Div2 certifications for use around a fueled aircraft, and integrate with existing aircraft health assessment systems. System must also be ruggedized for use in an operational environment including exposure to light dust, moisture, humidity, low and high temperatures, and salt fog conditions. In-depth investigations shall be conducted to create confidence on new approaches and methods. These in-depth validation and verification activities shall address user requirements including, but not limited to, human safety, reliability, operator fatigue, reparability, and robustness of the equipment to survive in a high tempo maintenance environment.

PHASE I: Demonstrate the feasibility of the prototype sensor system in a surrogate exhaust component environment. It must be able to operate on the specific types of high temperature thermal barrier coatings with relevant coating thicknesses. Any prototype sensor must meet field-level design requirements intended for a maintainer in the field (to include operation around a fueled aircraft, ergonomic, and safety requirements).

PHASE II: Building on Phase I demonstrated feasibility, the Phase II task will be to optimize the technology to advance the TRL/MRL. The Phase II prototype will be required to be demonstrated on a relevant scaled exhaust system with real or surrogate exhaust high temperature barrier coatings which will be provided by the Government. Spiral development will require development and feedback of usability of the sensor to meet field-level requirements for sensor ergonomics, software user interface, data analysis, and processing.

PHASE III DUAL USE APPLICATIONS: Determine a commercialization plan to demonstrate the technology for other applications or commercialize the product for other platforms and customers.

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REFERENCES:1. http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19910006077.pdf

2. http://onlinelibrary.wiley.com/doi/10.1002/tee.22255/pdf

KEYWORDS: cavity, coating, exhaust system, tailpipe, thermal barrier, thickness

AF171-104 TITLE: Portable, Localized Low Observable (LO) Coating Removal Tool

TECHNOLOGY AREA(S):

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a small, portable hand tool to measure outer mold line (OML) coating thickness and accordingly cut/score between 90%-95% of total coating thickness.

DESCRIPTION: To achieve the required performance metrics, OML coating systems contain material stack ups that are difficult to remove. When maintenance is required in areas where elastomeric coatings are present, the coatings must first be removed. The current process for OML coating removal in a localized area is scoring the outer layers by hand with a non-metallic scraper and pealing them away. This scoring process is labor and time intensive. There is a need to develop a handheld coating cutting/scoring process that can quickly and efficiently complete this process. Since the coating thickness varies, the tool must be capable of measuring the coating thickness in the area and cutting/scoring the coatings accordingly. It is not desirable to cut/score through the full coating thickness. The tool should penetrate between 90-95% of the material thickness to ensure no damage is incurred on the aircraft structure.

The current coating removal process cuts the outline of the area needed to be removed, then the coatings in that area are peeled away by hand. The intent of this tool is to follow the same coating removal process and simply accelerate the cutting/scoring process. The new cutting/scoring process must be capable of demonstrating cutting/scoring of elastomeric materials more efficiently when compared to current tools.

Past attempts to accelerate the cutting/scoring process have utilized metallic scrapers with a device to restrict the blade protrusion length to ensure that the coatings are not completely penetrated. However, this solution is unsatisfactory as the coating thickness varies. As a result, it is desired that a new tool be developed that can accurately measure the coating thickness and index the cutting/scoring device accordingly in real time. The coating thickness measurement portion must not damage the remaining coating material or the aircraft structure. The measurement device must be capable of identifying the interface of the aircraft structure and external coatings accurately to ensure that the cutting/scoring device will reliably penetrate 90- 95% of the coating thickness. Under no circumstances may the cutting/scoring device penetrate more than 95% of the coating thickness. The assumed coating thickness will be between 0.005 inches and 0.3 inches. The coatings will be of multiple layers with varying thicknesses.The goal of the end tool would be a handheld device easily used on the aircraft, including inside of engine inlet

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areas. There are no Government Furnished Equipment/Government Furnished Products (GFE/GFP) for Phase I or Phase II demonstration. Rather, demonstration can be conducted in the laboratory environment at the contractor's facility.

PHASE I: Compile a solution strategy documenting the complete proposed solution. Document and demonstrate the current capability of the proposed measurement method to determine the thickness of the OML coating system. The new process must be capable of determining thickness of various OML coatings.

PHASE II: Develop and demonstrate the capability to identify the interface between aircraft structure and the coating system to permit cutting/scoring 90-95% of the coating thickness. Under no circumstance may the tool penetrate more than 95% of the coating thickness. Demonstrate the feedback capability for various OML coatings and substructure types.

PHASE III DUAL USE APPLICATIONS: Demonstrate a stand-alone, handheld system capable of cutting/scoring 90-95% of OML coating system thickness where the thickness varies from 0.005 inches to 0.3 inches thick. The system must be portable and easily used on aircraft while demonstrating greater efficiency compared to current tools.

REFERENCES:1. Technical Order (TO) 1-1-8, Technical Manual, Application and Removal of Organic Coatings, Aerospace and Non-Aerospace Equipment, 23 April 2001.

2. Technical Order (TO) 1-1-691, Technical Manual, Cleaning and Corrosion Prevention and Control, Aerospace and Non-Aerospace Equipment, 2 Nov 2009.

KEYWORDS: maintenance, coatings, coating removal

AF171-105 TITLE: High Altitude Electromagnetic Pulse (HEMP) Protection for Nuclear Command and Control Communications (NC3) Systems

TECHNOLOGY AREA(S): Nuclear Technology

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop and demo capability to provide HEMP protection for C2 systems and power sources within Wing Command Posts (WCPs) or used by Mobile Support Teams (MSTs). This shield or barrier should prevent/limit HEMP fields & conducted transients from damaging Nuclear Command, Control, and Communication (NC3) systems.

DESCRIPTION: WCPs and MSTs are critical NC3 nodes that utilize fixed and mobile NC3 systems used for emergency action messaging (EAM). These systems require HEMP protection along with HEMP protection for their power sources in order to operate in a HEMP environment. The solution options may include shielding for

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systems/operations, penetration protection technologies for electrically conductive structures (building materials such as composites, concrete/stucco, conducting metals etc.), and special protective measures for non-conducting areas like ventilation routes.

PHASE I: Phase I shall produce a prototype to demonstrate the feasibility of the concept described above. Offerors may propose against the topic areas of (1) shielding for systems/operations, (2) penetration protection technologies for electrically conductive structures (building materials such as composites, concrete/stucco, conducting metals etc.), (3) special protective measures for non-conducting areas like ventilation routes.

For shielded systems focus area the offeror shall propose structural materials for HEMP shielding in accordance with the requirements referenced in MIL-STD-188-125 or MIL-STD-2169C. The Phase I effort should produce samples of sufficient size for testing against these standards (typically 14 x 14 in. or 26 x 26 in.). Testing can be accomplished by methods such as TEM cell measurements to mitigate costs. For the penetration protection technologies for electrically conductive structures, the offeror shall propose material based sealing solutions to complete the electrical pathway around the penetration and maintain the same level of shielding performance as the baseline wall from HEMP. Demonstration of this should be accomplished by before and after testing as defined in the MIL-STD-188-125. For the focus area of special protective measures for non-conducting areas like ventilation routes, the offeror shall demonstrate waveguide below cut-off or other standard airflow conditions. The offeror shall produce sections of ventilation at least 48 in. in length and 12 in. in diameter. Testing can be accomplished by free field testing methods. Offerors must be capable of acquiring Secret and Critical Nuclear Weapon Design Information (CNWDI) access by the end of the Phase I effort in order to be eligible for a Phase II award. If all technology areas are not addressed by one proposal, associate contractor agreements will be required during the Phase II.

PHASE II: Phase II shall produce one full scale (approximately 4 ft w x 6 ft l x 6 ft h) HEMP protection barrier kit in a WCP and on a MST that demonstrates the ability to reliably protect NC3 systems and their power sources from damage or degradation by threat-relatable transients. The system shall incorporate the technologies developed in the Phase I effort and demonstrate that they function as a system and not just as individual components. MILSTD-2169C shall be used as the validation testing and will be performed in coordination with Air Force or Army test capabilities. The offeror is to produce the structures as the deliverable and the government will provide validation testing.

PHASE III DUAL USE APPLICATIONS: Phase III shall analyze the solution set to ensure that the preventive maintenance, inspection, test, and repair activities to maintain HEMP hardness are feasibly retainable throughout its operational life cycle.

REFERENCES:1. MIL-STD-464:http://everyspec.com/MIL-STD/MIL-STD-0300-0499/MIL-STD-464C_28312/.

2. Nuclear Survivability Overview, DTRA:http://www.dtic.mil/ndia/2011CBRN/Franco.pdf.

3. DoD Nuclear Survivability Program (Kuspa):www.dtic.mil/ndia/2011CBRN/Kuspa.pdf.

4. Test Operations Procedure (TOP), 01-2-620 High-Altitude Electromagnetic Pulse (HEMP) Testing:www.dtic.mil/dtic/tr/fulltext/u2/a554607.pdf.

KEYWORDS: High-Altitude Electromagnetic Pulse (HEMP), emergency action messaging (EAM), EAM, HEMP, Mobile Support Teams (MST), MST, Nuclear Command, Control and Communication (NC3) systems, NC3, Wing Command Posts (WCP), WCP

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AF171-106 TITLE: Improved manufacturing and design of liquid electrolyte delivery systems

TECHNOLOGY AREA(S): Nuclear Technology

OBJECTIVE: Develop manufacturing and design capabilities that reduce cost and improve quality/reliability of remotely activated batteries.

DESCRIPTION: The development of manufacturing and design capabilities that will reduce cost and also improve quality/reliability of remotely activated batteries is sought. The anticipated advantage of improved manufacturing capability would be reliable design and repeatable manufacture of liquid electrolyte delivery to remotely activated batteries, including their corresponding flow paths and wicking/wetting capability. Current liquid electrolyte reserve batteries are built by carefully crafting and matching components to ensure capability and high reliability. Research into and improvements in gas generator and electrolyte delivery design and manufacturability could greatly improve lot to lot reliability and may lead to reduction in cost of future design and manufacture. This could be achieved by innovations in manufacturing process and its repeatability.

Possible applications include but are not limited to reentry vehicle, flight control, and guidance battery power. Areas of research focus should be gas generator design and composition consistency, electrolyte storage and flow characterization, residual pressure retention, backflow and pressure relief, cell material wicking and wetting improvements, and the repeatable manufacture of such components and battery characteristics.

PHASE I: Demonstrate proof-of concept for improvements in reliable and repeatable electrolyte delivery and wetting. Analyze various battery requirements and key performance parameters (battery capacity, internal leakage, rate capability, shelf life, etc.) and how they are improved by new delivery methods and their manufacture. As part of phase I, carefully benchmark the current state-of development.

PHASE II: Demonstrate significant improvements in the cited metric(s) from Phase I. Demonstrate compatibility of the chosen process technology with volume manufacture. Demonstrate integration of the metric-enhanced battery with some product target as mutually agreed upon by the offeror and the Air Force. Provide cost projection data to substantiate the design, performance, operational range, acquisition, and life cycle costs. Refine transition plan and business case analysis.

PHASE III DUAL USE APPLICATIONS: Demonstrate large volume manufacturability of various battery capacity and performance goals. The military applications include aerospace & naval emergency power, unmanned underwater vehicles (UUVs). Commercial applications include emergency power and other non-power long storage life applications.

REFERENCES:1. D. Linden and T.B. Reddy, eds., Handbook of Batteries, 3rd Edition, McGraw-Hill, New York, 2002.

2. Y. Li, H. Zhan, S. Liu, K. Huang, and Y. Zhao, J. Power Sources, Vol. 195, p. 2945, 2010.

3. A. Himy, Silver-Zinc Battery: Best Practices, Facts and Reflections, Vantage Press, Inc., 1995.

KEYWORDS: anode, battery, cathode, electrolyte, gas generator, missile power, remotely activated, reserve battery

AF171-107 TITLE: Continuously Self-Leveling Weapons-Storage Support Structure

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TECHNOLOGY AREA(S): Nuclear Technology

OBJECTIVE: Develop and demonstrate capability to continuously monitor and maintain an approximate 10 metric ton weapon support structure in a level state, while four (4) linear actuators cause it to ascend and descend. If not kept in a level state, binding and wear may result.

DESCRIPTION: The Weapons Storage and Security System (WS3) is capable of securely storing weapons in an underground vault. The weapon support structure is elevated by four linear actuators (jackscrews). During ascent and descent of the weapon support structure it is required that the weapon support structure remain level. A continuously self-leveling capability is required. As the WS3 vault operates to lift the weapons payload out of the underground vault, or to lower the weapons payload into the underground vault, the weapon support structure (~ 10 metric tons) is caused to ascend and descend by the action of four linear actuators (jackscrews) -- one on each corner of the support structure. During operation it is possible for the support structure to depart from a level state by more than the desired 1 mm, resulting in binding and excessive wear between the jack-lifting-bodies and the jack stems. The WS3 Program Office requires a project that will conduct research and development on a dynamic, real-time, distance measurement with precision on the order of 1mm over relatively short distances (1/2 meter to 3 meters). This shall be met by modeling (Phase I), and that will culminate in a demonstration full scale prototype of a vault-weapon-support-structure self-leveling capability, with precision no more than 5 mm difference between actuators and objective of no more than 1 mm difference (Phase II). The prototype shall be demonstrated in a WS3 vault.

PHASE I: Phase I shall produce a computer model that will demonstrate the approach and analyze the feasibility, precision, and sensitivity of the approach. The threshold for such a model is 5 mm difference in actuator level with an objective of 1 mm.

PHASE II: Phase II shall produce a full scale working self-leveling system that shall be demonstrated in a WS3 vault.

PHASE III DUAL USE APPLICATIONS: Commercial: Industrial condition that requires a self-leveling capability for massive loads supported and caused to ascend and descend via 4 linear actuators (jackscrews). Military: WS3 requires self-leveling capability for the massive structure that lifts and lowers the payload in and out of the underground vault.

REFERENCES:1. Valeria Artale, Cristina L.R. Milazzo, Calogero Orlando, and Angela Ricciardello, Genetic algorithm applied to the stabilization control of a hexarotor, AIP Conference Proceedings 1648, 780003 (2015); DOI: 10.1063/1.4912983View online:http://dx.doi.org/10.1063/1.4912983 and http://scitation.aip.org/content/aip/proceeding/aipcp/1648?ver=pdfcov

2. Dmitry Bazylev, Konstantin Zimenko, Alexey Margun, Alexey Rubtsov, ITMO University, Saint Petersburg, Russia, Adaptive control system for quadrotor equiped with robotic arm, Published in: Methods and Models in Automation and Robotics (MMAR), 2014 19th International Conference, 2-5 Sept. 2014, Page(s):705 - 710 ISBN:978-1-4799-5082-9

KEYWORDS: jackscrew, linear actuator, self-leveling, weapon support structure, Weapons Storage and Security System (WS3), WS3

AF171-108 TITLE: All-Fiber Optical Isolators for High Energy Lasers

TECHNOLOGY AREA(S): Materials/Processes

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OBJECTIVE: Develop magneto-optic materials and associated device designs for all-fiber optical isolators for use with single-fiber laser amplifiers emitting >5kW. These devices are needed for operation at laser wavelengths near 1µm and near 2µm.

DESCRIPTION: High power fiber lasers have made significant progress in the last several years, and as a result, powerful fiber lasers are now common in industry for a number of applications such as laser welding, laser cutting, and laser drilling. However, these lasers are not sufficiently powerful for many industrial and military applications, and one reason is that an all-fiber optical isolator, is still not available with sufficient power handling. Optical isolators absorb harmful back traveling reflections within an optical fiber system, in this case high power back traveling reflections that can harm components on the back end of the high energy laser system. The specific type of isolator here is all-fiber that do not contain an air gap. These devices are constructed from a rare-Earth-containing Faraday rotating fiber and a fused fiber polarizer. Commercially available all-fiber optical isolators operating at a wavelength of approximately 1 µm can handle forward and backward power of 50 watts and provide 1.5 decibels of isolation loss, but much higher power handling and reduced isolation loss are necessary for use with fiber laser amplifiers generating in excess of 5 kilowatts of laser power. The three most important overall characteristics of the resulting all-fiber optical isolator are power handling, optical loss, and the degree of isolation (throughput/input). The required specification from a successful Phase II effort follow. For 1µm, throughput power =300W, backward power =100W, insertion loss =1dB, and isolation =20dB. For 2µm, throughput power =50W, backward power =50W, insertion loss =1.5dB or less, and isolation =20dB.

PHASE I: Develop materials and optical isolator device designs for operation at 1µm and/or 2µm. Options include new magneto-optic materials or improvements to existing materials. Experiments shall indicate adequacy of the materials to meet the specifications given under the Description.

PHASE II: The contractor shall develop fabrication techniques for constructing all-fiber optical isolators with the specifications listed in the Description.

PHASE III DUAL USE APPLICATIONS: Military applications: airborne high energy lasers for aircraft self-defense Commercial applications: laser welding, laser cutting, and laser drilling.

REFERENCES:1. D.E. Zelmon, E.C. Erdman, K.T. Stevens, G. Foundos, J.R. Kim, and A. Brady, “Optical Properties of Lithium Terbium Fluoride and implications for performance in high power lasers,” Applied Optics 55 (2016), 834-837

2. L. Sun, S. Jiang, J.D. Zuegel, and J.R. Marciante 1, “All-fiber optical isolator based on Faraday rotation in highly terbium-doped fiber,” Optics Letters 35 (March 1, 2010), 706-708

KEYWORDS: optical isolator, magneto-optic materials, high Verdet-constant materials

AF171-109 TITLE: Structural Directed Energy and Nuclear Effect Mitigation of Composite Aeroshells for Munitions

TECHNOLOGY AREA(S): Nuclear Technology

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors

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are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Development, scale-up, and demonstration of munition relevant composite structural aeroshell materials designed to provide protection from directed energy, nuclear EMP, and nuclear particle effects.

DESCRIPTION: New material concepts are required for structurally integrated directed energy, nuclear electromagnetic pulse, and high energy nuclear particle protection for organic matrix composites. Directed energy for the purpose of this topic is defined as High Power Microwave (HPM) and High Power Laser (HEL) technologies. Nuclear particles for the purpose of this topic are defined as hot and cold x-rays, gamma rays, and neutrons. Materials submitted for consideration should be specifically designed for use on composite munition systems. Methods for incorporating the proposed materials into standard manufacturing processes such as braiding on a mandrel must be addressed. Protection materials must be incorporated into the structural buildup, not secondary applied or require additional non-standard manufacturing processes to fabricate.

New systems will require compliance with MIL-STDs, including 461, 464, and 3023, to meet the ever-changing mission environment. The metrics defined in the unclassified portion of the listed MIL-STDs will be used as evaluation criteria for the Phase I. Proposals to this topic must address the gaps in current composite materials’ ability to meet requirements such as those in the MIL-STDs list above. Relevant testing methods and techniques can be found in the "The Nuclear Matters Handbook, Expanded Edition" Appendix G4.1.[3] Proposed performance claims must be accompanied with supporting information or citation of available open literature or DTIC references. Materials proposed must be shown to be producible in large quantities, affordable, maintainable, and sustainable. Transition plans should include detailed discussion of material integration methods, cost relative to baseline materials, and maintainability/sustainability. Coordination with prime vendors and letters of support demonstrating the proposed transition pathway is highly encouraged.

Historically, technical efforts have focused on providing just one of the characteristics above; i.e. just HPM protection or just neutron protection. In this effort the composite must simultaneously provide protection from multiple directed energy and nuclear events while maintaining a weight near that of current composite material. Materials solution which add greater than 20% weight by volume over baseline composites

PHASE I: Propose, develop, and demonstrate flat coupons of scientifically relevant size (12 in. x 12 in. min.) to measure the performance of the composites under neutron, hot and cold x-ray, and directed energy environments. A design of experiments with specific materials and layups should be proposed, not just a review of the literature.

PHASE II: Build and demonstrate complex shapes of scientifically relevant size, in representative configurations, to measure the performance of the composites under neutron, hot and cold x-ray, and directed energy environments. Material should be a down selection from the design of experiment in Phase I. Specific platform based guidance and geometry will be provided in Phase II by the government.

PHASE III DUAL USE APPLICATIONS: Demonstrate the materials from the Phase II in a relevant environment and work with appropriate program office for transition and ground based simulated flight testing. Potential dual-use applications include shielding aircraft and spacecraft from cosmic radiation and electromagnetic environments.

REFERENCES:1. MIL-STD-464: http://everyspec.com/MIL-STD/MIL-STD-0300-0499/MIL-STD-464C_28312/.

2. Nuclear Survivability Overview, DTRA:http://www.dtic.mil/ndia/2011CBRN/Franco.pdf.

3. The Nuclear Matters Handbook, Expanded Edition:http://www.acq.osd.mil/ncbdp/nm/nm_book_5_11/index.htm.

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KEYWORDS: directed energy, DE, HPM, HEL, munition, electromagnetic pulse, nuclear, high power microwave, composite, organic matrix composite, BMI, epoxy, ceramic, ceramic composite, polymer matrix composite, carbon fiber, astroquartz

AF171-110 TITLE: Additive Manufacturing Process for High Resolution Conductive Traces

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop an additive manufacturing process capable of writing micron-scale features for frequency selective surfaces.

DESCRIPTION: For the protection of radio frequency (RF) systems from high-powered microwave (HPM), devices are being developed that require high-resolution features on the order of 3-5 microns. Thus far, photolithography has been the method of choice for the fabrication of these devices, using non-flexible substrates, such as silicon or glass. However, the use of inflexible substrates dictates that the devices are more readily placed into the near-field of the RF antenna where they may negatively affect the performance of the system, rather than into the far-field on a radome. Additive manufacturing is being explored as a method of integrating HPM countermeasures directly into or onto radomes. The radomes may be ceramic matrix composites (CMC) or polymer matrix composites (PMC), and the radome material and its operational environment dictate the material that can be written onto it. In the case of the CMC, which is used in high temperature applications, the FSS material must be capable of operation in the same environment as the CMC. For PMC radomes, the temperature requirements are less stringent and a larger variety of materials may be used. In high temperature applications, materials such as platinum cermet are used for the FSS. For PMC radomes, silver or copper based inks may be used. Inkjet, aerosol jet, and syringe pump direct-write are current state-of-the-art methods being used for depositing conductive traces but these methods have a realistic limit of 20-30 microns. Additionally, inkjet and syringe pump systems cannot write conductive traces conformally. Proposals are being sought to develop a technology which may utilize fully additive or a combination of additive and subtractive methods to create patterns with features and gaps of 3-5 microns. In a subtractive system, lasers may be capable of etching 10 micron gaps. While the basic requirement is for a system capable of meeting the specified resolution, the ability to perform the process conformally is beneficial and facilitates the creation of the patterns on radomes or other curved surfaces. This is a secondary requirement that may be addressed in successive phases of the SBIR. However, proposals for direct-write systems capable of conformal writing are preferred.

PHASE I: Phase I of this project would result in a design for an AM system with improved resolution over current capabilities. The objectives may be accomplished through an improvement/modification to a current technology or through a new methodology. The phase I would also result in the delivery of samples created on test equipment.

PHASE II: Phase II of the project will be the fabrication of a prototype system with a targeted 3-5 micron feature size. For cost purposes, this may be a system designed for the fabrication of two-dimensional patterns. A suitable demonstration of the device’s capabilities will be to fabricate a two-dimensional frequency selective surface. Samples of materials fabricated on the prototype will be deliverables.

PHASE III DUAL USE APPLICATIONS: Phase III of the project will be the fabrication of a prototype system capable of depositing a conformal pattern onto a radome or complexly curved surface.

REFERENCES:1. A. Mette, P. L. Richter, M. Hoteis, S. W. Glunz, “Metal Aerosol Jet Printing for Solar Cell Metallization,” Published online in Wiley InterScience, 5 April 2007.

2. B. King, M. Renn, “Aerosol Jet Direct Write Printing For Mil-Aero Electronic Applications,” Published online

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KEYWORDS: Directed energy, high powered microwave, direct write, additive manufacturing, radio frequency

AF171-111 TITLE: Nondestructive Quantification of the Degraded Elastic Modulus and Poisson's Ratio of Impact Damaged Polymer Matrix Composites

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Using single-sided inspection(s), nondestructively quantify the degraded elastic modulus and Poisson’s ratio in an impacted Polymer Matrix Composite (PMC) with a spatial accuracy of 0.01 in. and estimated properties NTE ±5% of those found via traditional mechanical testing.

DESCRIPTION: USAF methods to ensure aircraft structural integrity is maintained throughout designed service life are based on Damage Tolerance as defined in MIL-STD-1530C. Damage tolerance requires adherence to fail-safe, slow damage growth (preferred), or in special applications, safe-life design criteria. For typical USAF structural alloys, damage tolerance is achieved primarily via integration of fracture mechanics with slow damage growth criteria. Nondestructive inspections are performed at prescribed intervals during in-service operation to ensure adherence to the damage tolerance criteria, and ultimately the safety of the aircraft. With increasing application as primary and secondary aircraft structural components, efforts have been focused on enabling a life management approach for composites similar to that employed for metallic structures. However, the current shortfalls in composite damage progression models and nondestructive characterization methods require USAF composite structures to be designed and maintained to a no growth criterion for specified damage morphologies. Thus, to enable damage tolerance via slow damage growth for composites, further development of modeling and nondestructive evaluation (NDE) methods is required [1].

A nondestructive testing technique is sought to measure the mechanical properties of an impact damaged graphite fiber reinforced polymer matrix composite for input to damage evolution models. Previous research has shown some success in nondestructive measurement of mechanical properties of carbon-carbon [2] and carbon-fiber reinforced polymer composites [3] by means of ultrasonic testing. Reconstruction of the impact damaged state of composites has also been investigated and reported in the literature [4,5]. The desired solution shall combine nondestructive measurement of degraded mechanical properties of impact damaged PMCs with a spatial map of the damaged region via single-sided nondestructive testing. The method shall be demonstrated on PMC panels of layup and impact damage similar to those found in reference [1] and must localize regions of degraded elastic modulus and Poisson’s ratio within a voxel of dimension 0.05 in. x 0.05 in. x 0.05 in. (threshold) 0.01 in. x 0.01 in. x 0.01 in. (objective). Further, the measured properties shall be accurate within a threshold of ±10% and an objective of ±5% of those found via traditional mechanical testing, and generated property values shall not rely on baseline subtraction. Output(s) shall be provided in a generic, non-proprietary format capable of implementation within any commercial or non-commercial simulation tool.

The nondestructive quantification of degraded elastic modulus and Poisson’s ratio of impact damaged PMCs will be instrumental in providing the needed robust, predictive simulation capability for damage evolution of composite structures. This capability is a key enabler for sustainment of current and future USAF aircraft – providing structural integrity engineers the foundation to confidently, safely, and effectively manage the fleet over its lifetime while alleviating the no-growth certification requirement, which may be leaving performance and weight savings on the table.

PHASE I: Using single-sided nondestructive inspection(s) of an impact damaged PMC, localize regions of degraded elastic modulus and Poisson’s ratio within a voxel of equally-sized edges: 0.05 in. x 0.05 in. x 0.05 in. (threshold) 0.01 in. x 0.01 in. x 0.01 in. (objective). The method shall be demonstrated on PMC panels of layup and impact damage similar to those found in reference [1].

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PHASE II: Using single-sided nondestructive inspection(s) of an impact damaged PMC, quantify within a threshold of ±10% and an objective of ±5% the degraded elastic modulus and Poisson’s ratio localized within Phase I. The measured properties shall be verified against those obtained via traditional mechanical testing of the coupons employed in Phase I. Output(s) shall be provided in a generic, non-proprietary format capable of implementation within any commercial or non-commercial simulation tool.

PHASE III DUAL USE APPLICATIONS: Commercialize the tool/technique/method successfully developed in Phase II. Develop and document procedures for operation, calibration, and servicing. An example transition path is to partner with an AF system integrator to mature and demonstrate method in an operational environment.

REFERENCES:1. D. Mollenhauer, E. Iarve, K. Hoos, M. Flores, E. Zhou, E. Lindgren, and G. Schoeppner “Damage Tolerance for Life Management of Composite Structures – Part 1: Modeling,” Aircraft Structural Integrity Program Conference, 2015.

2. R.A. Kline, G. Cruse, A.G. Striz, and E.I. Madaras, “Integrating NDE-derived engineering properties with finite element analysis for structural composite materials,” Ultrasonics 31, pp. 53-59, 1993

3. A. Castellano, P. Foti, A. Fraddosio, S. Marzano, and M.D. Piccioni, “Mechanical characterization of CFRP composites by ultrasonic immersion tests: Experimental and numerical approaches,” Composites: Part B 66, pp. 299-310, 2014.

4. J.H. Gosse, and L.R. Hause, “A quantitative nondestructive evaluation technique for assessing the compression-after-impact strength of composites plates,” Review of Progress in Quantitative Nondestructive Evaluation 7B, pp.1011-1020

5. A.A. Fahim, R. Gallego, N. Bochud, and G. Rus, “Model-based damage reconstruction in composites from ultrasound transmission,” Composites: Part B 45, pp. 50-62, 2013.

KEYWORDS: polymer matrix composites, impact damage, nondestructive evaluation, mechanical properties, composite damage progression modeling, aircraft sustainment

AF171-112 TITLE: Thermal Modeling Base High-Temperature Polymer Matrix Composite (PMC) Structural Repair

TECHNOLOGY AREA(S): Materials/Processes

OBJECTIVE: Develop thermal modeling capability to enable selection of heating, cooling, and insulation approaches to be used in conjunction, for on-aircraft curing of high-temperature repair materials while preventing damage to existing structure and systems.

DESCRIPTION: Greater amounts of aircraft structures are being fabricated from high-temperature polymer matrix composites (PMCs) (such as those containing bismaleimide (BMI) and polyimide resins), as evidenced by B-2, F-22, and F-35 aircraft. If components fabricated from these materials cannot be removed from the aircraft and original performance must be restored, repairs must utilize materials that cure at high temperatures. This cannot typically be accomplished using current fielded technology.

In order to achieve maximum structural/temperature capability for a PMC repair and return an aircraft back to full operational capability, repair materials must be cured within recommended temperature ranges. Not doing so can affect the crosslinking process in the resin (composite matrix or adhesive) and potentially lead to in-service failures

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by producing structurally weak patches and/or adhesive bondlines. A relatively uniform temperature distribution is desired across a repair area, but this is usually difficult to achieve since complex aircraft structure often contain thickness variations (due to composite ply drop offs) and have underlying substructure that result in “hot” and “cold” regions in the repair. Higher cure temperatures make uniformity more difficult to achieve. Additionally, elevated temperatures and long isothermal dwell times required to cure high-temperature PMCs and associated adhesives can be detrimental to surrounding structure, systems, and/or coatings.

To ensure a repair will be exposed to the proper temperature profile, thermal surveys of the repair area are typically conducted. These establish the low and high temperature regions and guide placement of heating units and insulation, as well as any active cooling required to protect surrounding structure or systems. A proper thermal survey is a time-consuming, iterative process that involves placing many thermocouples (often 100 or more) in a mock-up repair configuration to generate an accurate thermal map that will dictate location of the relatively small number of thermocouples to be used to control and monitor the actual repair, ensuring a proper thermal profile. The “hot” thermocouple must accurately reflect the highest temperature in the repair region and is generally used to set the maximum temperature for the repair (to prevent damage) and the “cold” thermocouple is used to determine the length of cure time.

In the past, there have been several attempts to develop lower-temperature-curing materials that can yield high-temperature service performance, but these have not been successful. Alternate curing techniques (e.g., ultrasonic, electron beam, microwave, induction) have also been evaluated as another way to address this issue, but they too have not been practical for real-world application. The traditional heating/cooling approach used for low-temperature repairs could be viable to successfully cure high-temperature PMCs if the repair area’s thermal profile and thermal response were understood to an extent much greater than can be practically achieved using thermal surveys alone. A thermal modeling capability is required to determine heating, insulation and cooling (amounts and locations) to achieve proper repair material cure temperatures for various structures while preventing damage to existing structure and systems. This model would also guide location of critical thermocouples necessary for monitoring and regulating the cure process. A relatively few thermal surveys could verify the model’s output for a given application.

Benefit of developing this capability would be to improve the performance and increase confidence in high-temp PMC repairs while reducing the time to effect a repair.

PHASE I: Develop a prototype thermal modeling system capable of accurately predicting the thermal profile of a small high-temp PMC part (with metallic backside structure) going through a simulated repair. This would entail heating the repair material and bondline to near 440°F while not allowing the backside structure to exceed 270°F during the cure cycle.

PHASE II: Demonstrate thermal modeling system on a representative PMC aircraft structure at least 4 square feet in area for a simulated 2-inch through-hole per the temperature parameters denoted in the Phase I above. Also need to show how the system is adaptable/versatile for different structures. Procedures/approaches for practical implementation of active cooling and heating using currently available COTS equipment should also be a part of the demonstration.

PHASE III DUAL USE APPLICATIONS: Military – for on-aircraft repair of high-temperature PMCs (BMIs and polyimides). Commercial – for Out of Autoclave and Autoclave processing of PMCs, specifically that the model can predict the thermal response of complex tooling utilized in the manufacturing of PMCs

REFERENCES:1. FAA-H-8083-31 - Aviation Maintenance Technician Handbook - Airframe - Chapter 7: Advanced Composite Materials

2. "The Craft of Aircraft Repair", Composites World, May 1, 2005; compositesworld.com

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KEYWORDS: Composites, BMI, PMC, polyimides, curing, thermal modeling, on-aircraft, repair

AF171-113 TITLE: Solid-State Amplifier/Transmitter replacements for Travelling Wave Tube (TWT) Technology

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Increase availability, affordability, and reliability of amplifier components over current traveling wave tube (TWT) technology used in legacy missile warning/defense radars.

DESCRIPTION: Currently, missile warning/missile defense radar sub-systems suffer from diminishing sources of supply and support from OEMs. Some current radars, such as AN/FPS-108, rely on comparatively unreliable, inefficient, and outdated TWT amplifiers. Solid-state versions have demonstrated 10 times greater reliability with operational sustainment savings exceeding $100M over a 30-year lifetime for bomber radars. L-Band internally matched 250W to 1000W transistors are available from several sources. High power pulsed L-Band solid-state rack mounted power amplifiers, up to 800W power output, are commercially available. Development of higher pulse power solid-state L-Band power amplifier would be useful for military and commercial long range, search radar applications.

PHASE I: Conduct engineering study on solid state power amplifier replacement options. A systematic application of knowledge toward the production of useful materials, devices, and systems or methods, including design, development, and improvement of prototypes and new processes to meet missile warning/missile defense radar requirements. Complete system design for high power L-Band solid-state power amplifier (SSPA), and estimate performance characteristics, efficiency, and cost for 10 kW peak power L-Band SSPA.

PHASE II: Demonstrate solid state amplifiers can replace TWT amplifiers and their bulky, heavy, and expensive high voltage power supplies. Develop and demonstrate a prototype high pulse power solid-state L-Band power amplifier.

PHASE III DUAL USE APPLICATIONS: Integrate solid state amplifier into representative system to demonstrate capability.

REFERENCES:1.https://en.wikipedia.org/wiki/Cobra_Dane.

2.https://en.wikipedia.org/wiki/AN/FPQ-16_PARCS.

3.http://www.integratech.com/LBandR.aspx

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4.http://www.aethercomm.com/products/18

KEYWORDS: Solid State Radar Amplifiers, Traveling Wave Tube (TWT) replacements

AF171-114 TITLE: Enhancing Systems Engineering for Complex Systems with Digital Thread

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop integrated System-of-Systems design space to stitch design artifacts (e.g., electrical signals, digital logic, etc.) across individual systems into a System-of-Systems.

DESCRIPTION: This project addresses two aspects of the “Digital Thread & Digital Twin.” First, the ability to conduct Enterprise-Level System-of-Systems (SoS) engineering through a process/framework to transform capability gaps and Concept of Operations (CONOPS) into SoS capability requirements that can be allocated down to system level (e.g., platform, sensors, weapons, networks, etc.) programs. The second, is reduced acquisition process time associated with translation of capability documents into system requirements through improved decomposition, traceability, management of requirements provided by customers, and translation into technical requirements and acquisition documents. Complexity of integrated systems [2] (such as video surveillance, digital communications, and RADAR to name a few) necessitate new functional architectures, novel design tools, and innovative integrations technology to efficiently bring these complex components together. The challenge problem is exacerbated by industrial drive to leverage existing commercial-off-the-shelf (COTS) technology by unbundling capabilities and reintegrating systems together to form SoS. SoS are large-scale distributed collaborative systems, which are created through the integration of complex systems. SoS integration has an added challenge [3], as often times the sub-systems being integrated were never intended to be interfaced or controlled through other systems. The substantial complexity of SoS regularly results in mismatch between design and implementation of the integrated SoS. This mismatch stems from operational independence, managerial independence, evolutionary development, emergent behavior, and geographic distribution of SoS subsystems, and results in variability between subsystem design and SoS implementation.

Previous attempts to solve this problem [4, 5] have focused primarily on developing tools to address software application lifecycle management. These solutions are known as Application Lifecycle Management (ALM) tools, and include commercial examples, such as HP ALM, IBM Rational Team Concert, and Mylyn. The aim of ALM tools is to streamline the traceability of customer requirements all the way to test and release. ALM tools require significant human involvement to keep configurations up to date and manually make corrections when changes are flagged.

The envisioned solution for this research project could build upon technology developed for ALM, and extend it to system-level design. Some research has been conducted to extend ALM for use with system-level design [6], however does not scale to SoS-relevant problem sets. This effort seeks a SoS architecture design tool with the ability to describe both functional and integration artifacts (examples of these artifacts can be provided by the Government as needed) of systems through implementation of this Digital Thread. Solutions to this challenge are expected to

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dramatically decrease the time and effort required to design, integrate, and execute by providing a new mechanism to capture the totality of the SoS design in a unified digital form. This unified SoS design environment will provide a first-ever opportunity to conduct assessments of SoS performance in parallel with sub-system design, as opposed to the current approach which requires completed/executable sub-systems prior to SoS design in order to illicit performance information and make assessments.

PHASE I: 1) Broad Understanding of SoS architectural design tools.2) Specific understanding of how sub-system trades affect SoS capabilities/performance.3) Approach to link commercially accepted electrical signal and digital logic design artifacts (e.g., DoDAF).4) Ability to synchronize different digital artifacts and link design changes to performance across SoS.

PHASE II: Demonstrate ability to implement Digital Thread to realize a SoS architecture, and show how design changes within sub-systems impact SoS capability. Develop and demonstrate the utility of Digital Thread to realize a SoS architecture. Show scalability of the Digital Thread solution to realize SoS architectures of military relevance. The capability of this Digital Thread must extend to support most commercial digital artifacts.

PHASE III DUAL USE APPLICATIONS: Develop a mechanism to realize integrated SoSs with dual-use applications, such as surveillance systems and safety applications. A number of government agencies (military and civil) require this capability to protect facilities, operations, critical infrastructure and personnel.

REFERENCES:1. Sage, A. P., & Cuppan, C. D. (2001). On the systems engineering and management of systems of systems and federations of systems. Information Knowledge Systems Management, 2(4), 325-345.

2. Jain, R., Chandrasekaran, A., Elias, G., & Cloutier, R. (2008). Exploring the impact of systems architecture and systems requirements on systems integration complexity. Systems Journal, IEEE, 2(2), 209-223.

3. Oberhauser, R., & Schmidt, R. (2007). Towards a Holistic Integration of Software Lifecycle Processes Using the Semantic Web. In ICSOFT (ISDM/WHAT/DC), 137-144.

4. Mihindukulasooriya, N., García-Castro, R., & Esteban-Gutiérrez, M. (2013, October). Linked data platform as a novel approach for enterprise application integration. In Proceedings of the Fourth International Conference on Consuming Linked Data-Volume 1

5. Balarin, F., Watanabe, Y., Hsieh, H., Lavagno, L., Passerone, C., & Sangiovanni-Vincentelli, A. (2003). Metropolis: An integrated electronic system design environment. Computer, 36(4), 45-52.

KEYWORDS: Digital Thread, system architecture, system(s)-of-systems, system integration, design tools

AF171-115 TITLE: 3-D Antenna Technology using Additive Manufacturing

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US

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Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Survey state-of-the-art technology for additively manufactured antennas to form a conformal active aperture with integral active components embedded in the phased array, and propose an innovative solution to implement it on an airborne platform.

DESCRIPTION: Fabrication of printed circuit board (PCB) based antennas typically involves the patterning of dielectric substrates with conductive material. For predominantly 2-D applications, PCBs are the prototyping solution of choice, combining material removal through machining and etching with material addition by soldering and plating. Despite the use of vias and other multi-layering techniques, it is predominantly a planar process. Consequently, a large percentage of existing three dimensional electromagnetic designs have been assembled from multiple PCB layers to increase the dimensionality.

In the last decade, there has been a marked increase in the documented use of 3-D electromagnetic devices, including gradient index lenses at both microwave and optical frequencies, and radio frequency lenses that attain resolution beyond the diffraction limit. While these structures are more complex, making fabrication considerably more difficult, we are now able to realize them by taking advantage of advances in macroscopic layered prototyping, through technologies such as stereolithography, selective laser sintering, fused deposition modeling (FDM), and three-dimensional printing. These methods are capable of addressing the needs of 3-D electromagnetic designs which incorporate non-planar geometries and material inhomogeneity. The use of 3-D rapid manufacturing for functional electromagnetic devices, however, is still uncommon, as the simultaneous layering of conductive and insulating materials remains difficult.

While there is much published work related to 3-D printing and other rapid manufacturing, most deal with topics of strictly mechanical interest. The successful implementation of functioning antennas will benefit the customization of RF solutions greatly. Applications range from flexible RF devices that can be contoured to the shapes of various objects, to complicated systems such as a fully functioning doubly conformal active electronically scanned array (AESA).

This topic seeks to advance the state of the art on additively manufactured antennas (elements and active arrays) using specifically 3-D rapid additive manufacturing, including 3-D printing, stereo lithography, FDM, and other relevant methods. The geometrical focus is ultimately 3-D/non-planar devices and structures rather than those that can be designed and fabricated using conventional PCB methods.

In particular, the key objectives are:

1) Advancement of processing methods and available materials in terms of substrate loss (loss tangent less than 0.01), thermal and environmental stability (for soldering, autoclave, vacuum molding applications, and extreme environments), selective metallization (conductivity within a factor of 2 when compare with bulk metal of similar cross section at a given frequency, spatial resolution at better than 0.5% of the wavelength at the operating frequency)

2) Exploitation of concurrent 3-D elements (Non-planar broadband elements with full metal and/or mixed metalized and dielectric materials) and conformality (Conformal to doubly curved surface with varying curvature in different directions and small radius of curvature with respect to wavelength)

3) Multilayered conformal structures that incorporate vias and RF transmission lines (for example microstrip and waveguide structures) with good adhesion and mechanical stability

4) Incorporation of active and passive elements such as resistors, capacitors, inductors, transistors, and various integrated components in different packages within the multilayered conformal structure.

Transition of this technology will include the development of a broad band conformal antenna array with steering

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capability.

PHASE I: Design and model an 8x8 element X-band single polarization antenna array with>10% bandwidth on a truncated surface of an ellipsoid with radius of curvature less than 5 wavelengths. The design should be digitally steerable to at least +/-45 degrees in 1 direction (2 preferable), and incorporate one RF port. Key performance parameters must be analyzed and compared to a multilayered planar solution. Key fabrication methods should be identified and demonstrated.

PHASE II: Phase II shall mature the technology from Phase I and a multilayered conformal device as well as a planar version of the design should be delivered. The device should have one RF port and a control port. The programming language for the control should be MATLAB, with the appropriate hardware to control the beam steering included. The agility of the steering should correspond to a pointing accuracy within the 3 dB beamwidth for a slant range of 5 km at 150 m/s.

PHASE III DUAL USE APPLICATIONS: Industry partnership and transition of the technology for dual use in domestic commercial space, air, and/or ground sensing systems as well as DoD platforms is to be accomplished.

REFERENCES:1. Adams, J. J., Duoss, E. B., Malkowski, T. F., Motala, M. J., Ahn, B. Y., Nuzzo, R. G., & Lewis, J. A. (2011). “Conformal Printing of Electrically Small Antennas on Three-Dimensional Surfaces.” Advanced Materials, 23(11), 1335-1340.

2. I. M. Ehrenberg, S. E. Sarma, and B.-I. Wu, “A three-dimensional self-supporting low loss microwave lens with a negative refractive index,” J. Appl. Phys., vol. 112, art. no. 073114, Oct. 2012.

3. Isaac M. Ehrenberg, Sanjay E. Sarma, and Bae-Ian Wu, “Fabrication of an X-band conformal antenna array on an additively manufactured substrate” 2015 IEEE APS/URSI International Symposium, Vancouver, Canada, July 19–25, 2015.

4. Jeffery W. Allen and Bae-Ian Wu, “Design and fabrication of an RF GRIN lens using 3D printing technology,” SPIE Photonics West 2013, San Francisco, CA, Feb. 2–7, 2013.

KEYWORDS: 3D printing, antennas, array

AF171-116 TITLE: Scalable Coherent Photonic Array on a Silicon Platform

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

OBJECTIVE: Design and fabricate a scalable, coherent photonic array on a silicon platform.

DESCRIPTION: Once considered inexhaustible, fiber channel capacity is presently limited by the bandwidth of erbium-doped amplifiers (~10THz). While amplification over wider bands is possible, at least in principle, by using a Raman or parametric process, deployable communication infrastructure is likely to remain bound to the conventional C and L bands in the foreseeable future. Consequently, to increase spectral efficiency while transmitting in a strictly limited spectral range, coherent transceivers will be exclusively used in all practical cases of interest to the DoD. Indeed, coherent signal processing already dominates advanced wireless, fiber communication [1], and other sensing [2] applications. Coherent systems are also of particular interest to other DoD applications such as free-space communications [3] and sensing links where an optical signal cannot be amplified mid-span. This limitation greatly reduces the utility of incoherent (On-Off) schemes except for very low bandwidth and/or very high-power applications. For example, coherent receivers play a central role in modern LIDAR/LADAR systems [4]

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which strive for high sensitivity, wavelength agility, and jamming resistance.

Although a coherent communication link can be terminated by a single coherent receiver, this is not an acceptable option when bandwidth or wavelength diversity is required. For example, in LIDAR/LADAR systems, the ability to launch and simultaneously receive multiple, mutually coherent carriers can be leveraged to offset the deleterious effects of atmospheric scintillation and prevent band-specific jammers. Likewise, in multi-path-interference (fading) communication links, wavelength multiplexing can maintain channel capacity even under adverse conditions. More importantly, when signal processing diversity requires deserialization of high-bandwidth signals and full access to both quadratures, multiple coherent receivers must be used in a synchronized array structure.

With the recent progress made in integrated photonics and optoelectronic packaging, it is now possible to combine sources, arrayed waveguide routers, and even digitizers (ADC) on a single silicon platform (albeit heterogeneously). While these technologies can be easily used to realize a single-channel coherent transceiver, a scalable coherent receiver array is still a challenge. If scalable coherent receivers can be built to co-exist with complementary metal-oxide-semiconductor (CMOS) blocks, not only would conventional LIDAR/LADAR and communication links be greatly improved, but a number of other DoD-relevant capabilities would also be enabled including a new class of robust/compact channelizers. This initiative seeks the proof-of-principle design and fabrication of a highly scalable coherent array on a silicon platform and is expected to develop in following Phases.

PHASE I: Design and model an integrated silicon photonics based coherent array with a minimum of 60 emitters. Each emitter should have a side-mode suppression ratio greater than 45 dB, an emitter-to-emitter spacing greater than 100 GHz, and a per-emitter optical power of at least 200 microWatts. Preference will be given to designs of reduced complexity and footprint, to those with higher degrees of coherence within and across the emitters, and to systems with higher wall-plug efficiencies. Any electronic control required for array power and noise stabilization must be based on clear technical assumptions, factored into the design, and modeled.

PHASE II: Prove the fabrication viability of the proposed solution using a silicon foundry to generate prototypes. The Phase II work is also expected to improve upon the Phase I design with the goal of scaling beyond 100 channels, increasing power, and increasing the emitter-to-emitter spacing. To ensure this technology can be developed into a commercial product, Phase II is expected to use commercially available lithography tools (not e-beam) through a foundry such as AIM Photonics. The resulting system must be tested against the criteria noted in Phase I including the relevant coherence measurements.

PHASE III DUAL USE APPLICATIONS: Two separate applications for this technology (commercial/military) should be targeted by designing and demonstrating ruggedized/fieldable prototype units that include any/all electronic control(s). Specifically, the unit should suffer minimal performance degradation when subjected to temperature fluctuations, shock, and vibration.

REFERENCES:1.  Toyoda, et al., "Marked Performance Improvement of 256 QAM Transmission Using a Digital Back-propagation Method," Opt. Express 20, 19815-19821 (2012).

2.  M. Ghavami, L. B. Michael, and R. Kohno, “Ultra Wideband: Signals and Systems in Communication Engineering,” (Willey, 2007).

3.  A. Kordts, et al., “Higher order mode suppression in high-Q anomalous dispersion SiN microresonators for temporal dissipative Kerr soliton formation,” Opt. Lett. 41, 452-455 (2016).

4.  See for example:http://www.menlosystems.com/products/optical-frequency-combs/fc1500-250-uln/

5.  V.W.S. Chan, "Free-space Optical Communications," J. Lightwave Technol. 24, 4750-4762 (2006).

6.  S. C. Weitkamp (Ed.), “Lidar: Range-Resolved Optical Remote Sensing of the Atmosphere,” (Springer, 2005).

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KEYWORDS: Coherent Communications, Electronic Warfare, Optoelectronic Integration, Channelization, LIDAR/LADAR

AF171-117 TITLE: Multi-Sensor/Multi-Platform Integration and Sensor Resource Management

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: To create algorithms to support distributed unmanned air vehicle (UAV) swarm sensing management via an Autonomous Resource Manager (ARM) to plan the sensing operations of many multi-spectral sensors across many platforms to meet pre-defined mission objectives.

DESCRIPTION: There are several operational concepts where a large aircraft deploys smaller UAV’s to provide sensing capability in A2/AD environments including clearing paths for high value assets (HVA) by coordinated suppression of enemy air defenses (SEAD) and destruction of enemy defenses (DEAD). Groups of UAVs that can be deployed from carrier and other platforms to perform missions in Anti-Access/Area Denied (A2/AD) environments is an emerging area of research. These groups of UAVs need to be controlled with minimal impact to the current mission and workload of the crews of the HVAs that deploy them and, if required, be able to carry out pre-defined mission objectives without contact with the HVAs in the area. There is ongoing research in autonomous control swarming UAVs from a collision avoidance perspective, but very little in sensor control. As far as resource management, the state of the art is single ship man-in/man-on-the-loop. There has been little to no work in the area of sensor resource management coordinated across multiple platforms. The objective of this topic is to address the control of UAV platforms in a swarm from a sensing perspective. The goal is to put the appropriate sensors in the correct locations to complete pre-defined mission objectives. This objective is to be completed assuming working collision avoidance, appropriate sensors, appropriate data links, and integrated auto-pilot. The ARM will utilize and augment the capability of these existing systems.

The ARM should control the positions of the UAVs and their corresponding sensor look angles based on pre-defined mission objectives and real-time threat information. The scenario for this topic is an HVA clearing mission. The UAV swarm should reveal, surveil, detect, and return category 2 targeting coordinates (7-15 meter CEP90) to the HVA to target the IADS and proceed into the A2/AD environment. To accomplish this mission, a composition of platforms that each host a single sensors type including electro-optic/infrared (EO/IR), synthetic aperture radar (SAR), radio frequency direction finding (RFDF), electronic support (ES), electronic attack (EA), and long range communications. The ARM should coordinate the positions of each of the sensors to effectively complete the mission objective with the intact swarm and after attrition of any of the functional sensors. The ARM should be able to effectively work through no threat environments, jamming environments, and active engagement from the threat resulting in swarm attrition. The ARM should be distributed across the swarm and be able to coordinate the swarm for resilience against attrition and sensor failures. The ARM should account for sensor type when determining actions of each sensor. Different sensors will require different tasking to accomplish seemingly similar tasks. The ARM should be scalable to operate on Group 1 through Group 5 UAVs and any size swarm with an emphasis on smaller (Groups 1 and 2) platforms and moderate size swarms (10-20 platforms). If restricted to Group 1 and 2 UAVs, the payload including sensor, data product processing, and ARM processing should be 2 to 15 pounds. A

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survey of COTS sensors and understanding of processing requirements for various data product outputs should be conducted as part of this topic, but is not the focus. The focus is to develop the ARM algorithms in a Size, Weight, and Power (SWaP) configuration on appropriate processing (Field Programmable Gate Array (FPGA), in situ with commercial auto-pilot, Central Processing Unit (CPU), etc.).

PHASE I: Develop ARM algorithms to coordinate sensing across multiple platforms as outlined in the description. Propose a mix of sensor types for a swarm of 10 UAVs. Develop a processing architecture for the ARM and sensor data products. Create a laboratory test plan for execution in Phase II to demonstrate performance in “focusing mission” by being able to defeat a generic air defense system. Present an architecture for 2 sensor types that meets a 15 pound payload requirement.

PHASE II: Build two prototype processors to test in a laboratory configuration. Demonstrate that the ARM is capable of accomplishing the focusing mission in a laboratory environment by showing coordination across the systems and an appropriate level of abstraction of sensor inputs and output for integration with a UAV and COTS sensors for Phase III. Develop a flight test plan to test the ARM using 3-4 UAVs. Explore other extensions of the ARM processor for distributed coherent sensing applications or other interest areas as coordinated with the customer.

PHASE III DUAL USE APPLICATIONS: Develop a transition strategy for the ARM processing capability. Conduct a flight test with three (3)-four (4) UAVs to verify the functionality of the ARM for the focusing mission and other mission as determined by the sponsor or performer. If applicable, implement other extensions of the ARM processor as documented in Phase II.

REFERENCES:1.  Small Unmanned Aircraft Systems (SUAS) Flight Plan: 2016-2036;http://www.af.mil/Portals/1/documents/isr/Small_UAS_Flight_Plan_2016_to_2036.pdf

2.  L. Geng, Y. F. Zhang, P. F. Wang, J. J. Wang, J. Y. H. Fuh, and S. H. Teo, "UAV surveillance mission planning with gimbaled sensors," 11th IEEE International Conference on Control & Automation (ICCA), Taichung, 2014, pp. 320-325. URL:http://ieeexplore.ieee.org.wrs.idm.oclc.org/stamp/stamp.jsp?tp=&arnumber=6870939

3.  F. Barbaresco, J. C. Deltour, G. Desodt, B. Durand, T. Guineas, and C. Labreuche, "Intelligent M3R Radar Time Resources management: Advanced cognition, agility & autonomy capabilities," 2009 International Radar Conference "Surveillance for a Safer Wor

4.  P. E. Berry and D. A. B. Fogg, "On the use of entropy for optimal radar resource management and control," Radar Conference, 2003. Proceedings of the International, 2003, pp. 572-577.doi: 10.1109/RADAR.2003.1278804. URL:http://ieeexplore.ieee.org.wrs.

5.  T. Hanselmann, M. Morelande, B. Moran, and P. Sarunic, "Sensor scheduling for multiple target tracking and detection using passive measurements," Information Fusion, 2008 11th International Conference on, Cologne, 2008, pp. 1-8. URL:http://ieeexplore.

KEYWORDS: Sensor resource management, radar, EO/IR, Unmanned Aerial Systems (UAS)

AF171-118 TITLE: Develop a Small Pitch LADAR Receiver for Low SWAP Sensing

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

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The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Design, fabricate, and test laser detection and ranging (LADAR) sensor laser and detector components for 3-D imaging. The technologies should be designed to support operations from a platform with tight size weight, power, and cost (SWAP-C) constraints.

DESCRIPTION: The AF has a need to develop sensors to support Globally Integrated Intelligence, Surveillance, and Reconnaissance (GIISR) and Global Precision Attack (GPA) capabilities. This includes the development of high sensitivity, very narrow field of view optical sensors for target identification. Typical sensing scenarios cue the LADAR to an object or location to collect a sequence of return pulse measurements. This measured data may be processed for immediate display in the cockpit, downlinked to an image analyst, and/or sent to an automatic or aided target recognition system. Current linear mode and Geiger mode receivers in production or under development provide good sensitivity and clocking rates in large format arrays, as indicated in Reference 1 and 3. Recent linear mode receivers are designed to provide clock rates on the order of nanoseconds, while Geiger mode receivers an order of magnitude faster. Pixel pitch of production receivers are < 100 um, while newer development nears 30 um. Sensitivity of large array linear mode receivers has not reached the capability of counting photons. Ranging performance and sensitivity are primary drivers in the receiver.

In an effort to improve LADAR focal plane arrays (FPA), this topic seeks to reduce the size of the unit cell in the readout integrated circuit (ROIC) of a linear mode or Geiger mode LADAR and improve detector sensitivity of avalanche photodiodes (APD), minimizing detector pitch while improving sensitivity and range precision. Of interest are new design ideas for timing circuits and noise suppression. The goal of the unit cell design is to develop a high bandwidth (BW) detector with single photon detection sensitivity, capable of providing 2-D imagery, with high dynamic range for generation of 3-D point clouds with improved range estimation performance. It is envisioned that innovation in the detection logic and timing circuitry may address this challenge, however all approaches are of interest. Performance goals include noise equivalent input < 10 photons, single photon sensitivity, detection BW of GHz to THz at short scene depths, capable of imaging scene depths from 30 m to over 500 m, provide data to support video frame rates of > 20 Hz, in a 1024 x 1024 format or larger array with pixel pitch < 30 um operating in the 1 to 2 um wavelength region. Low crosstalk, large dynamic range > 10 bit, cooling, and damage threshold are considerations. A focus on the development of APDs or ROIC is acceptable, with a requirement of developing a path toward integration and completion of a full LADAR receiver. Initial design should be 16 x 16 format or larger.

The detection circuit logic for each unit cell is expected to be the same for the entire array, but could be implemented to provide various detection methods such as first surface, first and last surface, multiple surfaces, etc., supporting imaging though obscurants such as camouflage netting. The LADAR receiver would be capable of being triggered from a pulsed laser, potentially digitizing the outgoing pulse. Cost and SWAP for the full receiver would need to be considered for the final design, where low cost insertion into small unmanned aerial vehicles (SUAV) is a goal. As a threshold, a receiver with supporting electronics should fit into a 4” x 4” x 4” volume, and the cost of a complete LADAR system < $250k.

No required use of Government materials, equipment, facilities or data is envisioned.

PHASE I: Develop design ideas for unit cells, detection logic, detectors, and laboratory test configurations for fabrication of a direct detection LADAR receiver and provide circuit simulations. Develop a program plan, Statement of Work (SOW), and performance expectations for a small format 16 x 16 or larger receiver, scalable to 1024 x 1024 or larger. Develop a commercialization plan.

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PHASE II: Design, develop, and test a 16 x 16 format or larger LADAR receiver capable of photon counting. Provide laboratory test results, details of test methods. Deliverable includes small format LADAR receiver with supporting electronics for laboratory testing. A focus on the development of APD’s or ROIC is acceptable. Develop a program plan, SOW, and performance expectations for a large format receiver capable of insertion into an SUAV, targeting pod, or turret.

PHASE III DUAL USE APPLICATIONS: Design, develop, and test a large format receiver capable of flight testing a brassboard system in an airborne laboratory type environment. Develop a program plan to integrate into a targeting pod or turret and perform flight testing. Explore integration into SUAV’s and fielded systems.

REFERENCES:1. Reference 1) Michael Jack; George Chapman; John Edwards; William Mc Keag; Tricia Veeder; Justin Wehner; Tom Roberts; Tom Robinson; James Neisz; Cliff Andressen; Robert Rinker; Donald N. B. Hall; Shane M. Jacobson; Farzin Amzajerdian; and T. Dean Cook; Advances in LADAR Components and Subsystems at Raytheon. Proc. SPIE 8353, Infrared Technology and Applications XXXVIII, 83532F (May 1, 2012).

2. Reference 2) Mark A. Itzler; Mark Entwistle; Mark Owens; Ketan Patel; Xudong Jiang; Krystyna Slomkowski; Sabbir Rangwala; Peter F. Zalud; Tom Senko; John Tower; and Joseph Ferraro; Design and performance of single photon APD focal plane arrays for 3-D LADAR imaging. Proc. SPIE 7780, Detectors and Imaging Devices: Infrared, Focal Plane, Single Photon, 77801M (August 17, 2010).

3. Reference 3) Xiaogang Bai; Ping Yuan; James Chang; Rengarajan Sudharsanan; Michael Krainak; Guangning Yang; Xiaoli Sun; and Wei Lu; Development of high-sensitivity SWIR APD receivers. Proc. SPIE 8704, Infrared Technology and Applications XXXIX, 87042H

4. Reference 4) Beck JD, Scritchfield R, and Mitra P, et al; Linear mode photon counting with the noiseless gain hgcdte e-avalanche photodiode. Opt. Eng. 53(8), 081905 (Apr 25, 2014).

KEYWORDS: LADAR, photon counting, 3-D imaging

AF171-119 TITLE: NIIRS 9 Small Unmanned Aircraft System (SUAS) 5-Inch Gimbal

TECHNOLOGY AREA(S): Air Platform

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a National Imagery Interpretability Rating Scale (NIIRS) 9 capable 5 inch gimbal suitable for Common Launch Tube (CLT)-compatible SUAS platforms.

DESCRIPTION: Small Unmanned Aircraft Systems (SUAS) are proliferating across the USAF. They fit into the USAF Intelligence, Surveillance, and Reconnaissance (ISR) strategy by providing local persistence, operation in contested environments, and low probability of detection. As the utility of SUAS is demonstrated, demands on their

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performance increases.

SUAS small gimbals currently achieve NIIRS 6-7 but not NIIRS 9. Small gimbals are greatly impacted by environmental conditions and aircraft vibrations. Traditional stabilization techniques are difficult to implement in small gimbals. Improved imaging performance is dependent on the camera and optics that make up the sensor system. All of these are constrained by Size, Weight, and Power – Cost (SWaP-C) limitations.

This effort seeks a 5” diameter gimbal suitable for Common Launch Tube (CLT)-deployed SUAS of less than 50 pounds operating at a typical slant range of 1500 feet and altitude of 200 feet and higher. The gimbal shall provide full-color visible-band images and full-color motion video (T). It shall provide the operator with situational awareness, target detection and tracking, and an on-gimbal multi-mode video autotracker (T). This might be accomplished by providing simultaneous, sequential, or selectable NIIRS 9 chip-outs and a motion video stream.

The visible-band images/chip-outs shall achieve NIIRS 9 (T). NIIRS defines and measures the quality of images and the performance of imaging systems. Although primarily applied in the evaluation of satellite imagery, it provides a systematic approach to measuring image quality. NIIRS 9 would allow an analyst to “Identify (read) vehicle registration (license plate) numbers (VRN)”.

The NIIRS 9 images shall be: visually lossless after transmission (T); have a minimum frame rate of 0.5 (T) - 5 (O) hertz; have ground coverage sufficient to fully encompass the rear aspect of a vehicle (pickup truck) (T) - 20 x 20 feet (O) at the range/altitude above.

The motion video field-of-view (FOV), resolution, image latency, and frame rate shall allow the operator to maintain scene situational awareness, search for, detect, and manually and automatically track vehicle targets and dispersed personnel (T).

Motion video and NIIRS 9 capability should be provided simultaneously (O). The FOVs shall be operator-steerable over a large part of a lower hemisphere field-of-regard (T). The imaging system(s) shall have focus, non-uniformity correction, color balance, gamma, aperture and exposure control with no or limited operator intervention (T). The resulting data stream(s) shall be transmissable over existing SUAS-capable encrypted digital datalinks (T). The NIIRS-9 data stream shall not interrupt or degrade pointing accuracy, autotracking capability, image stability (T), or measurably degrade operator situational awareness (O).

This effort won’t develop new gimbal structures, but will develop a payload, and processing capability. An off-the-shelf gimbal or mature prototype is the expected starting point. This gimbal shall support typical SUAS maneuvering (orbits, racetracks, fly-bys) and fly-ins, and shall compensate for disturbances due to gusts and air turbulence. The gimbal should provide accurate line-of-sight pointing data, on-gimbal inertial measurement, and interface to platform GPS to allow for 10-15 meter Circular Error (CE90) geo-coordinate accuracy at range (T).

This effort will include both hardware and software approaches to providing a complete 5” gimbal package. Hardware solutions may include improved stabilization and pointing accuracy of the gimbal. This effort should not require focal plane array development, but take advantage of current state-of-the-art.

PHASE I: Identify hardware requirements for the gimbal, including stabilization, optics, processor, and imager. Consider software approaches and algorithms as appropriate. Prepare a preliminary design of the gimbal and payload. Use modeling and simulation to justify performance. Conduct requirements and design reviews (SRR, PDR). Demonstrate critical subsystems using representative hardware if possible.

PHASE II: Perform detailed design of the gimbal and payload. Conduct a Critical Design Review. Continue modeling and simulation of system performance. Build a prototype gimbal and payload. Provide all safety of flight data required by USAF and/or FAA authorities. Conduct a Test Readiness Review. Evaluate performance in laboratory (T), tower (T), motion base (O) and flight test (O) environments. Flight test on contractor surrogate preferred. A tower test location will be provided by the Government.

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PHASE III DUAL USE APPLICATIONS: Refine design based on outcomes of tests and customer feedback in Phase II; develop a manufacturing plan and/or select a partner for production of 5” gimbals.

REFERENCES:1.  Air Force Unmanned Aerial System (UAS) Flight Plan 2009-2047,http://www.govexec.com/pdfs/072309kp1.pdf

2.  USAF Intelligence Targeting Guide,http://fas.org/irp/doddir/usaf/afpam14-210/part13.htm.

3.  Common Launch Tube Technology,http://www.systima.com/

4.  Design of a Tube-Launched UAV,https://www.researchgate.net/publication/267377594_Design_of_a_Tube-Launched_UAV

KEYWORDS: SUAS, Imaging, NIIRS

AF171-120 TITLE: Direct Measurement of Targeting Coordinates from Small Unmanned Aerial Systems (SUAS) EO/IR Gimbal Systems

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop software and hardware solutions to enable direct measurement of targeting coordinates from gimbals mounted on SUAS.

DESCRIPTION: Accurate, timely, and reliable targeting is critical for Air Force strike operations. Fighter aircraft and reconnaissance platforms use high performance targeting pods (Sniper and LITENING) and gimbals (Multispectral Targeting System) to provide this capability. However, new USAF strategies are increasingly relying on Small Unmanned Aircraft Systems (SUAS) to provide situational awareness and targeting information. See for example the Loyal Wingman concept envisioned in the AF SUAS Flight Plan, whereby SUAS provide lethal strike support to their lead aircraft with “…real-time precision targeting.”

The high performance targeting pods and gimbals on larger aircraft take advantage of the Direct Method for obtaining targeting coordinates. This approach relies on the accurate knowledge that these sensor systems have of their three-dimensional state data (altitude, position, and orientation) acquired from their Inertial Measurement Units (IMU) and Global Positioning Systems (GPS) sensors, combined with a laser rangefinder for information about the object of interest. While this approach is appropriate for large gimbals that have the available Size, Weight, Power, and Cost (SWaP-C) to host the required high-quality sensors, these large and expensive sensors are not a possibility for SUAS.

The object of this topic is to demonstrate a <5” gimbal generating own-camera metadata information and range estimates sufficient to enable targeting. The goal is to achieve Cat-1 level targeting coordinates as specified in reference 1 at slant ranges of less than 2km (threshold, 5km objective), together with the uncertainty information for any geo-location estimate to verify its accuracy. This effort will include both hardware and software approaches meeting the targeting requirements for a SUAS. Hardware solutions may include improved stabilization and pointing accuracy of the gimbal and sensors. Software solutions may include using video information provided by the sensor system in order to reduce errors in the extrinsic (location and attitude) and intrinsic (focal length) calibration values of the camera. This approach is made possible by recent advances in processing with multi-core processors developed for the cell phone industry. Video outputs from this gimbal should be standards compliant, including MISB 1107 data as required for targeting.

While the specific targeting application will not be as applicable outside of the military, approaches to provide better

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geo-positioning and uncertainty estimates will be of use in non-military applications.

PHASE I: Identify the hardware requirements (including sensor performance) needed to achieve desired gimbal performance. Develop software approaches and algorithms for reducing errors three-dimensional state data. Design prototype 5” gimbal. Perform modeling and simulation to justify targeting coordinate and uncertainty accuracy.

PHASE II: Continue modeling and simulation to improve software approaches, algorithms and hardware performance. Based on these results, build or modify a prototype 5” gimbal. Evaluate gimbal performance in laboratory and flight test environments.

PHASE III DUAL USE APPLICATIONS: Refine design based on outcomes of tests and customer feedback in Phase II; develop a manufacturing plan and/or select a partner for production of 5” gimbals.

REFERENCES:1. Joint Publication 3-09.3, "Close Air Support", http://www.public.navy.mil/fltfor/ewtglant/Documents/courses/cin/TACP%20Docs%20K-2G-3615/JP%203-09.3%20CAS%20Jul%2009.pdf

2. Andersen, ED and Taylor, CN. “Improving MAV pose estimation using visual information,” in Proceedings, IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS), 2007.

3. Li, M and Mourikis, A. “Vision-aided inertial navigation for resource-constrained systems,” in Proceedings, IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS), 2012.

KEYWORDS: Targeting Coordinates; SUAS; Geolocation

AF171-121 TITLE: Integrated Circuit (IC) Die Extraction and Reassembly (DER) for More Complicated ICs

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Evaluate performance, reliability, and safety of more complicated circuits repair (e.g., repair of hybrids and modules using extracted die). Develop new techniques to perform assessment as needed.

DESCRIPTION: Die Extraction and Reassembly (DER) has been successfully demonstrated for monolithic military integrated circuits (see AF161-142). Hybrid integrated circuits and multichip modules (that are out of production and without sources of supply) are being repaired by replacement of internal semiconductor die. The die needed for repair are often obsolete. Die extraction offers a low-cost, quick reaction solutions for repairing critical parts from many legacy aircraft and space systems.

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Background on DER:DoD and extreme-condition commercial applications continually face diminishing manufacturing sources and material shortages due to obsolete electronics parts. As the number of available ICs in the appropriate package from franchised/trusted sources goes to zero, the community has few options. Currently, the options are: new manufacturing of the original outdated IC, reverse engineer the IC function, and either emulate the IC die with more current technology, or fabricate a redesigned die. Other options include circuit board redesign, or worst case, system level redesign. Redesigns usually take well over a year and can cost tens of million dollars for each substitute die, circuit board, or system design.

If the needed IC is available but not in the required package, recently another option has emerged. The process is called DER. Typically the same die is supplied in many different packages. The DER process takes a die equivalent to the obsolete die from an undesirable package and reassembles that die into the needed package, hybrid or module. The oil drilling industry’s need for high-reliability, high-temperature electronics drove early development of the DER process. The goal was to take parts in low-cost stress-sensitive plastic packages, developed for systems with benign operating conditions and re-package them for use in extreme, high stress environments. The DoD has similar requirements but the DER techniques have not been certified so as to ensure DER part meet mil grad requirements. Furthermore, the tools, techniques, and knowledge needed to certify DER parts for military use are still in development. Innovations are sought to develop tools and techniques that will eventually lead to a certification process similar to those in place for MIL-STD-883 compliant parts. Also innovators are sought to develop the necessary physics based analytical and testing techniques to determine the operating and environmental limits of digital and analog die of different technology families, complexities, functions/performance, from different vendors and die foundries following die extraction and repacking processing.

Care must be taken to ensure ICs match the CAD model parametric for best circuit operation. Military detail specifications often have fewer specified parameters and looser parametric limits than those found in commercial data sheets, though both commercial and mil versions were assembled using the same die. Military equipment designers use part level CAD models that match the parametric content of that part vendor's commercial specification.

PHASE I: Define and document a manufacturing process for DER ICs.

Document an expected return on investment (ROI) with a goal of 3:1. Build/test a hybrid IC that uses at least one DER IC or a complex field programmable gate array (FPGA). Testing shall demonstrate as closely as possible full compliance with MIL-STD-883, including all military detail specification Table I electrical/timing limits.

PHASE II: Document an expected ROI. Develop a specific process for an obsolete IC for an identified aircraft. Perform software, physical, environmental, and dynamic modified life testing on it. Demonstrate DER processes are sufficiently stable and controllable so as to ensure military-grade like parts can consistently be produced. Record parametric data when screening ICs. Determine if DER IC reliability is improved by selecting die that more closely matches the manufactures CAD model parametrics.

PHASE III DUAL USE APPLICATIONS: Use Phase II processes to develop/test DER ICs for use on two aircraft (as different as possible) to resolve reliability and/or diminishing manufacturing sources (DMS) issues. The techniques developed under this topic will be documented to enable the U.S. Government/commercial sector to easily leverage the benefits of this effort.

REFERENCES:

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1. Environmental Requirementshttp://www.dla.mil.- Military Standard (MIL-STD) 883J - Test Method Standard, Microcircuits- MIL-STD 750 - Test Methods for Semiconductor Devices- MIL-PRF-38510 - General Specification for Microcircuits- MIL-PRF-19500 - General Specification for Semiconductor Devices- MIL-PRF-38534 - General Specification for Hybrid Microcircuits- MIL-PRF-38535 - General Specification for Microcircuits

2. Defense Logistics Agency (DLA) Approved Test Facilitieshttp://www.landandmaritime.dla.mil/Offices/Sourcing_and_Qualification/labsuit.aspx.

3. Statement of Work for Die Extraction/Reassembly Process, AFRL Validation Effort, 21 Aug 2015, F-16 Program Office, Wright Patterson AFB OH.

4. Patented DPEM Process for Die Removal, DPA Components International (Simi Valley, CA)http://www.dpaci.com/patented-dpem-process-for-die-removal.html.

5. Die Extraction Strategy Solves DMSMS Challenges, Global Circuit Innovations (Colorado Springs, CO)http://www.cotsjournalonline.com/articles/view/102446.

KEYWORDS: integrated circuit, IC, microcircuit, Die Extraction and Reassembly, manufacturing, obsolescence, diminishing manufacturing sources, reliability

AF171-122 TITLE: V/W-band Accelerated Life Test System

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a V/W-band accelerated-temperature radio frequency (RF) life test system for multi-channel testing of solid-state power amplifier device technologies.

DESCRIPTION: Future V-band and W-band high data-rate satellite communications concepts and related space electronics developments require the lifetime assessment of advanced millimeter-wave solid-state technologies. Assessment results from life test systems provide an indication of advanced millimeter-wave transistor processes’ viability for long-term space application. However, integrated RF accelerated life test (ALT) systems are currently not commercially available for these frequencies. Required is the innovative development of multi-channel RF ALT systems that include low-insertion-loss test fixtures to address V-band (71-76 GHz) and W-band (81-86 GHz) frequencies. The integrated test system should include the RF drive and driver amplifiers required for future life testing of representative Standard Evaluation Circuits (SECs) in the developed system’s V- and W-band WR-12 (60-90 GHz) test fixtures. RF drive considerations should consider the possibility of single-stage SECs, including millimeter-wave single-stage gallium nitride monolithic integrated circuits. The integrated system should further

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include software monitoring/control of the hardware’s dc and RF inputs and outputs, as well as temperature control and monitoring of baseplate temperatures of the devices-under-test. Independent control and monitoring of each channel’s device-under-test should be addressed with the integrated multi-channel RF ALT system.

PHASE I: Concept design of a multi-channel accelerated-temperature life test system for V/W-band life testing of power amplifier technologies and related standard evaluation circuits (SECs). The design concept should include low-insertion-loss test fixtures to support the RF drive required for 71-76 GHz and 81-86 GHz testing over the life test system’s baseplate temperature limits.

PHASE II: Assembly, test and development of the prototype multi-channel, accelerated-temperature V/W-band life test system designed in Phase I, as well as the demonstration of the prototype low-insertion-loss test fixtures designed in Phase I.

PHASE III DUAL USE APPLICATIONS: The life test systems would support the assessment of advanced RF power transistor processes for military space, airborne, and ground applications and further support the assessment of advanced RF power transistor processes for commercial space, airborne, and ground applications.

REFERENCES:1. P. Vassiliou, Understanding Accelerated Life-Testing Analysis, 2003 Annual Reliability and Maintainability Symposium, 2003.

2. B. Barr, High Temperature, High Power RF Life Testing of GaN on SiC RF Power Transistors, MA-COM Technology Solution White Paper.

KEYWORDS: RF lifetesting, accelerated temperature, space electronics

AF171-123 TITLE: Dual Ka/Q-Band Low Noise Amplifiers

TECHNOLOGY AREA(S): Space Platforms

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop dual Ka-band and Q-band low noise amplifiers for satellite communications (SATCOM), point-to-point digital radios, and wideband receiver applications.

DESCRIPTION: Signal noise poses a significant challenge to long-distance satellite communications, impacting bit error rates, the level of transmitter radiated power required to close the link, and, indirectly, the payload size, weight and power. The purpose of this topic is to develop dual Ka/Q-band, innovative, state-of-the-art low-noise amplifiers (LNAs) using advanced low-noise Monolithic Microwave Integrated Circuit (MMIC) processes to demonstrate compact, producible, dual-band Ka-band and Q-band LNAs for space and terrestrial applications. This topic is intended to support research exploring the best approach and process for achieving low noise and high gain over both Ka and Q-band with optimum linearity (measured by the output third-order intercept point, or OIP3, across the

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frequency of operation). The goal is to demonstrate the ~2 dB noise figure level-of-performance that can currently be achieved in separate Ka-band and Q-band low-noise amplifiers for satellite application, but instead accomplish this noise figure performance in a single dual-band LNA. Overall performance goals include simultaneous operation at Ka-Band (27.5 to 31.0 GHz) and Q-Band (43.5-47 GHz), with noise figure at room temperature <2.0 dB, small signal gain >20 dB, input and output return loss better than -10 dB, power consumption <500 mW, IIP3 >5 dBm, OIP3 >25 dBm, and RF input survivability of 1W. An operating temperature range -40 to +85 degrees C is anticipated. The total dose radiation tolerance goal is 300 krad (Si).

PHASE I: Design a dual Ka-band and Q-Band MMIC LNA meeting the objectives identified above. Validate the LNA design through modeling and simulation.

PHASE II: Fabricate the LNA MMIC design(s) for dual Ka-band and Q-band. Characterize for amplifier noise, gain, linearity, and power consumption under typical operating conditions.

PHASE III DUAL USE APPLICATIONS: Military low noise amplifiers for these frequency bands will support WGS and AEHF follow-on satellites and point-to-point digital radios. Commercial LNAs operating at these frequencies will support commercial millimeter-wave wireless and wideband receiver applications.

REFERENCES:1. Armengaud, V., Laporte, C., Jarry, B., Babak, L., “27–31 GHz MMIC low noise amplifier with filtering functions for space communication system,” 19th International Crimean Conference, 14-18 Sept. 2009.

2. Qiangji Wang, Yunchuan Guo, “Ka-band self-biased monolithic gaas pHEMT low noise amplifier,” Microwave Technology & Computational Electromagnetics (ICMTCE), 2011.

3. Qian Ma, Leenaerts, D., Mahmoudi, R., “A 30GHz 2dB NF low noise amplifier for Ka-band applications,” Radio Frequency Integrated Circuits Symposium (RFIC), 2012.

4. Yu-Lung Tang, Wadefalk, N., Morgan, M.A., Weinreb, S., “Full Ka-band High Performance InP MMIC LNA Module,” IEEE MTT-S International Microwave Symposium, 2006.

5. Moyer, H.P., Kurdoghlian, A., Micovic, M., Lee, T., “Q-Band GaN MMIC LNA Using a 0.15µm T-Gate Process,” Compound Semiconductor Integrated Circuits Symposium, 2008.

6. Schwantuschke et al; “Q- and E-band Amplifier MMICs for Satellite Communication,” IMS 2014, June 2014.

KEYWORDS: Ka-band, Q-band, LNA, MMIC

AF171-124 TITLE: Ultra-Endurance UAV

TECHNOLOGY AREA(S): Air Platform

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon,

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gail.nyikon@us.af.mil.

OBJECTIVE: Produce a low cost, ultra-long endurance (>7 day) Unmanned Air Vehicle (UAV) suitable for intelligence, surveillance and reconnaissance (ISR) missions.

DESCRIPTION: Unmanned air vehicles play an important role in today’s military operations. They are invaluable in locating time critical targets, reporting enemy positions and movements to battlefield commanders, and destroying tactical targets. One important aspect of these operations is the ability to provide persistence in monitoring an area of interest. Most of the current UAV’s are designed to remain in flight for time periods of 20-40 hours, primarily limited by fuel capacity. This creates a deployment and logistics challenge for battlefield commanders to maintain eyes on target for extended periods of time, which is usually achieved by deploying multiple waves of UAVs.

The objective of this topic is to develop a low cost UAV with very long endurance, of at least seven days, that would enable the ISR mission to be accomplished with reduced manpower and system resources (esp. number of vehicles) to maintain near continuous coverage. Operating footprint should minimize personnel and hardware as compared to other UAV systems. Notionally the UAV will transit from its launch point to the area of interest nominally several hundred miles away, and loiter in that region for the mission duration, although the ability to move quickly between nearby areas of interest is also desired. The UAV should provide the capability to fly at 10,000-15,000 feet AGL, with a payload of 250lbs and 2000W power requirement. The system must be able to operate in 50 knot winds aloft, with minimal degradation in range and endurance or deviation from the area of interest. The system must also demonstrate minimal acoustic and visual signature to be virtually undetectable by ground personnel. The system must also be able to transit light to moderate icing conditions associated with climbing and descending through stratus cloud layers containing known icing conditions. The system does not need to loiter for prolonged periods in icing conditions. Typical take-off profiles are constant slope and minimum altitude changes are required once on profile.

A number of possible technologies can be considered to meet this requirement, but it is anticipated that the most likely candidates include hybrid power systems, solar power, and possibly power harvesting. Other technologies such as conventional airships (may not meet winds aloft requirement), laser power transmission (difficult to provide laser transmission to remote areas of interest), and tethered aircraft (no flexibility to move to remote areas) may not be suitable unless innovative approaches can be developed to overcome their limitations for the envisioned missions.

Some key desired capabilities of the system are:• Allow for >7 day vehicle endurance capabilities• Support payloads of 250lbs while supplying 2000W• Transit from launch location to area of interest up to several thousand miles and return safely• Maintain ‘orbit’ over area of interest in most weather conditions, but primarily winds aloft of up to 50 knots and intermittent light to moderate icing conditions• Acoustic and visual signature should be virtually undetectable by unaided ground personnel• Operate on logistically available fuels (diesel, Jet-A, Mo-Gas, etc.)• Suitable for military operational environments, including typical site constraints and runway sizes in Forward Operating Bases (FOB)• Minimal maintenance required in comparison to typical UAVs• Minimum personnel and hardware footprint as compared to other UAS• System cost to include the UAV, Broadband SATCOM, launch/recovery system (if any), fueling system (if unique), etc. < $1M

PHASE I: The contractor shall provide trade studies and engineering design necessary to define the operational system & associated technologies. The contractor shall show evidence that key enabling technologies are adequately mature (e.g., Technology Readiness Level >=6). Key enabling technologies shall include propulsion system, electrical power generation, flight control adequate to control necessary endurance parameters, energy storage, & anti-icing systems if required.

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PHASE II: The contractor shall develop and test a UAV that provides the capability to loiter over an area of interest for >7 days.  The test program shall culminate in a demonstration, on a government test range, of >7 days endurance at representative altitudes, carrying payload and mass simulators totaling 250 lbs.

PHASE III DUAL USE APPLICATIONS: The various technologies developed in Phase II are applicable to military and government applications. There are potential commercial applications in a wide range of diverse fields that include airborne communication nodes for cellular communications, crop monitoring, and site security.

REFERENCES:1.  “Effect of power system technology and mission requirements on high altitude long endurance aircraft”, Colozza, Anthony J. NASA Report Number NASA-CR-194455, 1994.

2. “Low Reynolds number, long endurance aircraft design”, Foch, R. & Ailinger, K. AIAA, Aerospace Design Conference, Irvine, CA, 3-6 February 1992.

3. “High Altitude Long Endurance Air Vehicle Analysis of Alternatives and Technology Requirements Development” Craig L. Nickol and Mark D. Guynn and Lisa L. Kohout, Thomas A. Ozoroski, 45th AIAA Aerospace Sciences Meeting, Reno, NV, 8-11 Jan. 2007.

KEYWORDS: long endurance air vehicle, unmanned aerial system, UAV, airborne surveillance, persistent intelligence surveillance and reconnaissance

AF171-125 TITLE: Aerial Refueling of UAVs

TECHNOLOGY AREA(S): Air Platform

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Radically increase mission length and on-station availability of Unmanned Air Vehicles (UAVs) by developing capability to conduct air-to-air refueling (AAR) of Groups 4 and 5 UAVs with calibrated airspeeds of 130 KCAS or less.

DESCRIPTION: Unmanned air vehicles play an important military role for locating time critical targets, reporting enemy positions and movements to battlefield commanders, and destroying strategic targets or lethal ground systems. Additionally, these unmanned systems are being designed to remain in flight for time periods of multiple days or more. Unfortunately, returning to base of operations to obtain additional fuel creates a deployment and logistics challenge.

Boom-and-receptacle and probe-and-drogue are the two hardware configurations and methods commonly used for AAR. In the former, a refueling boom on the rear of the tanker aircraft is steered into the refueling port on the receiver aircraft. In this method, the job of the receiver aircraft is to maintain proper position with respect to the

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tanker. With the probe-and-drogue method, the tanker aircraft trails a hose with an aerodynamically stabilized flexible “basket” or drogue. The receiver aircraft has a probe that must be placed or docked into the drogue. This is the preferred method for small, agile aircraft because the equipment is small and lightweight, and a human operator is not required on the tanker aircraft.

One of the challenges faced in AAR is minimum airspeed. For this effort the focus will be Groups 4 and 5 UAVs with maximum airspeeds of 130 KCAS. In order to maximize potential on-station capability, it is desirable to minimize the distance the UAV must travel in order to reach the refueling orbit. Since many military UAVs operate inside hostile territory, bringing a large manned tanker into this arena is problematic. Because of this, an unmanned, automated tanker could a potential solution.

There are five (5) key technical challenges associated with AAR of UAVs:

1. The refueling procedure will require the UAV to operate in close proximity of the tanker aircraft. Therefore, it is critical for at least one of the aircraft to know, with a high level of accuracy, where it is relative to the other.

2. UAV and tanker must avoid collisions with each other.

3. One or both the tanker and UAV must respond quickly if an unsafe refueling condition occurs.

4. From a cost, maintenance, and availability point of view, minimize modifications to both the tanker and the UAV, e.g., avoid changes to structural members, and try to keep size and weight of refueling hardware under 3%.

5. The refueling system must operate under broad weather conditions and day and night conditions.

This list of technical challenges is not all inclusive. Rather, there are additional technical challenges such as, redundancy or contingency management, beyond line of sight communications between the tanker, UAV and their operators, and full airspace collision avoidance. These issues are beyond the scope of this program and will not be addressed; however, the architecture chosen should lend itself to accommodate these challenges in the future.

For this effort, offerors should consider both the tanker and UAV for how a potential refueling system will work. One element of the problem is for the system to be applicable to unmanned refueling aircraft, rather than existing manned tankers (e.g. KC-135). Offerors should also consider automation of probe/drogue deployment and retraction, coordination between unmanned systems (cooperative control), and possible influence (flight dynamics or other) of a smaller tanker aircraft, if any.

PHASE I: The contractor shall conduct an AAR concept study of Groups 4 and 5 UAVs with maximum airspeeds of 130 KCAS that demonstrates: (A) feasibility of proposed system architecture, (B) minimal impacts to proposed tanker/UAV combination, (C) feasible AAR concept of operations, (D) capability to control the systems, and (E) risk analysis of proposed concept.

PHASE II: The contractor shall demonstrate the following: (A) Ability for both aircraft to rendezvous at the designated refueling point, (B) Ability to safely operate both aircraft in close proximity to each other, (C) Ability to transfer fuel from the tanker aircraft to the UAV, and (D) Ability to conduct mission planning.  All of this will be done and require minimal modifications to either aircraft.  Cooper Harper Ratings or a similar approach for qualifying “goodness” shall be used.

PHASE III DUAL USE APPLICATIONS: The contractor shall pursue commercialization of the various technologies developed in Phase II for potential government applications. There are potential commercial applications in a wide range of diverse fields that include cargo, resupply, airdrop, or ISR type missions.

REFERENCES:1. Nalepka, J. P., and Hinchman, J. L., “Automated Aerial Refueling: Extending the Effectiveness of Unmanned Air Vehicles,” AIAA Paper 2005-6005, 15–18 Aug. 2005.

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2. Tandale, M.D., Bowers, R., and Valasek, J., “Trajectory Tracking Controller for Vision-Based Probe and Drogue Autonomous Aerial Refueling,” Journal of Guidance, Control, and Dynamics, Vol 29, No 4, July-August 2006, pgs 846-857.

3. U.S. military UAS groups. In Wikipedia. Retrieved September 19, 2016, fromhttp://en.wikipedia.org/wiki/U.S._military_UAS_groups

4. Cooper-Harper Rating Scale. In Wikipedia. Retrieved September 19, 2016, fromhttps://en.wikipedia.org/wiki/Cooper%E2%80%93Harper_rating_scale

KEYWORDS: air to air refueling, probe and drogue, refueling boom, autonomous operation, flight controls, unmanned air vehicle, unmanned aircraft system, vision based sensing, remotely piloted vehicle, aircraft conversion, drone

AF171-126 TITLE: Integrable high-performance analog optical modulators

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop integrated analog photonic modulator components compatible with photonic foundry production.

DESCRIPTION: The advent of foundry-based integrated photonic circuit technology has opened up a significant design space for system engineers designing analog photonic signal processing circuits. In the commercial world, communication systems such as radio over fiber or proposed 5G architectures benefit from analog signal processors, while the military can find use of it in electronic warfare and RADAR signal processing applications. Photonic foundry design libraries provide a large number of components that can be used to create complex and functional circuits. Nevertheless, the two primary integration platforms silicon and Indium Phosphide (InP) have yet to be fully exploited for analog signal processing and the lack of reliable linearized analog optical modulators with broad bandwidth operation in a compact form is one of the reasons. Many RF system analyses indicate that low optical losses, low drive voltages, linearity, and wide bandwidth operation are still best addressed using commercial off-the-shelf lithium niobate modulators. One possible option would be the hybrid integration of thin film lithium niobate, which may provide better RF analog system performance than the integrated modulators available today at the cost of integration complexity.

In order for RF analog signal processing fully benefiting from integrated photonic circuit platforms, integrable optical modulators are needed (including, but not limited to, silicon, InP, lithium niobate, and others) low optical losses of less than 4 dB per modulator, low drive voltage of less than 2V, broad bandwidth of at least 50 GHz, and a high spur-free dynamic range of at least 120 dB-Hz2/3. The modulators need to be able to be integrated with other optical components compatible with photonic foundry design platforms to demonstrate analog RF signal processing capabilities in a packaged, compact form.

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PHASE I: Demonstrate that the choice of material for achieving the desired modulator performance metrics is compatible and integrable with photonic foundry material platforms such as silicon or InP.

PHASE II: Fabricate and integrate the compact modulators with silicon or InP based integrated circuits and demonstrate the described modulator performance in any analog system of choice (e.g., an RF optical link) in integrated circuit form. In particular, compact designs and approaches that do not limit back end of the line (BEOL) options are sought.

PHASE III DUAL USE APPLICATIONS: Transition the modulator structure manufacturing technique to a photonic foundry. Develop packaging techniques for the analog system of choice to demonstrate ruggedized prototype units that should suffer minimal performance degradation when subjected to temperature fluctuations, shock, and vibration.

REFERENCES:1. Qi Li et al, “High-Speed BPSK Modulation in Silicon”, IEEE Photonics Technology Letters, Volume 27, Issue 12, Page: 1329-1332.

2. Ashutosh Rao et al, “Heterogeneous Microring and Mach-Zehnder Modulators Based on Lithium Niobate and Chalcogenide Glasses on Silicon”, Optics Express, 24 Aug 2015, Volume 23, No 17.

3. J. S. Barton et al, “Monolithically Integrated 40 Gbit/s Widely Tunable Transmitter Using Series Push Pull Mach Zehnder Modulator SOA and Sampled Grating DBR Laser”, Optical Fiber Communication, 2005 OM3.

KEYWORDS: RF integrated Photonics, Integrated Optical Modulators, radio over fiber, Electronic Warfare, Microwave Photonics, RADAR

AF171-127 TITLE: Programmable Feed to Enable Low Frequency Measurements in Small Compact Far-Field Antenna Ranges

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop a feed network for use in compact far-field ranges to extend the lower frequency cutoff of ranges with smaller reflectors.

DESCRIPTION: Smaller compact far-field ranges suffer from the inability to measure lower frequency targets due to the size of the range and the size of the reflector used in the range. The edge treatment of the reflector is chosen during its design for a certain low frequency cutoff and utilizing the reflector below that frequency can introduce secondary scattering terms that cannot be removed by hardware time gating and/or software time gating. To measure lower frequency targets engineers would need to design and build a much larger compact far-field range with a larger reflector designed for a specific frequency cutoff goal. Large compact far-field ranges serve the purpose of

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measuring lower frequency targets, but using a large compact range for prototypes is an inefficient use of the ranges time and can introduce extra costs and scheduling issues for the prototype measurements.

Utilizing a programmable feed that includes phase and amplitude control offers the ability for a smaller compact range to measure targets with lower frequencies than can be accommodated by the use of the main reflector. A programmable feed that includes phase and/or amplitude control can give the degrees of freedom necessary to create a plane wave at lower frequencies using a smaller reflector than required for a given frequency, but without the secondary scattering terms.

This program will develop a programmable feed that would add a measurement capability down to 1 GHz to a Government far-field compact range utilizing a reflector designed for a frequency cutoff of 4 GHz. This far-field compact range features a 7'x6' reflector with a 7.5' focal length. The programmable feed would be capable of producing a plane wave that has < +/- 5 degree phase ripple and < +/- 1 dB amplitude taper and < +/- .25 dB amplitude ripple across a 3 ft wide target.

The programmable feed, if successful, could give several Government and Industry groups the capability of utilizing, or building, a smaller compact far-field range and be capable of measuring lower frequency targets than were possible before, saving costs on the design/fabrication on a larger reflector and range structure that would typically be required. It would also allow more Industry groups the capability of owning their own compact-range instead of renting time in larger ranges, potentially saving costs and schedules for current and future programs. These programs could be both Government-funded programs or Commercial applications.

PHASE I: Phase I will investigate conceptual design for a programmable feed to determine feasibility and perform simulations towards an appropriate feed antenna/array, antenna/array structure, and the amount of phase and amplitude control required to create a plane wave for a specific compact range scenario.

PHASE II: Phase II will design, model, fabricate, and test a programmable feed for application as a feed antenna in a compact far-field range. It is also anticipated that the applicability to other small far-field compact range geometries will also be demonstrated with the designed system.

PHASE III DUAL USE APPLICATIONS: Phase III will develop a programmable feed antenna that would be capable of being implemented in a variety of Government and Industry compact far-field ranges.

REFERENCES:1.  McKay, J.P.; Rahmat-Samii, Y., An array feed approach to compact range reflector design, in Antennas and Propagation, IEEE Transactions on, vol.41, no.4, pp.448-457, Apr 1993

2.  H. Wang, J. Miao, J. Jiang, and R. Wang, "Plane-wave synthesis for compact antenna test range by feed scanning," Progress In Electromagnetics Research M, Vol. 22, 245-258, 2012.

KEYWORDS: Phased Array, Compact Far-Field Range, Antenna Measurement

AF171-128 TITLE: Advanced Analog-to-Digital Converter for GPS Receivers

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type

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of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop an advanced analog-to-digital converter (ADC) that enables >100 megasamples per second (MSps) & up to 350 MSps with 16 effective number of bits (ENOB) conversion for GPS receivers. Design should limit cycle latency & minimize power and complexity.

DESCRIPTION: The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 3.5.b.(7) of the solicitation.

Ground, airborne, and sea GPS receivers in contested environments with high-dynamic range requirements need high-resolution data converters (ADCs and DACs) to maximize signal-to-noise ratio (SNR) and anti-jam (AJ) performance within navigation bands. While there are non-ideal effects, the effective number of bits of the converter is primarily a function of the signal-to-noise and distortion ratio (SNDR or SINAD). The highest resolution converters currently available have approximately 13 to 14 ENOB and typical SNDR of approximately 80 dB, which is insufficient for desired GPS applications. Current commercial high speed 16-bit analog-to-digital converter (ADC) topologies can operate at 100 MHz and higher conversion speeds, but they do not perform with 16 ENOB across the desired bandwidths.

The USAF is interested in this development for use in a digitally-processed GPS receiver with strong anti-jam performance. The focus of this effort will seek to develop an ADC architecture with the following capabilities:

1. 100 MSps (T)/350 MSps (O) sampling speed

2. 16 ENOB across all desired frequency bands

3. Covers all navigation bands (with emphasis on just above L1 center frequency to just below L2 center frequency)

4. Minimized power and complexity

5. Architecture shall also be compatible/portable to existing commercial Integrated Circuit (IC) processes

Proposals should clearly indicate how the result of the effort would be shown to improve military GPS receiver capabilities through a test and validation plan. Testing and validation of risk reduction components of the overall effort is encouraged in Phase I.

Offerors are encouraged to work with military GPS receiver prime contractors throughout the effort/program to help ensure applicability of their efforts and begin work towards technology transition.

Offerors should clearly indicate in their proposals what government furnished property or information are required for effort success. Requests for other DoD contractor intellectual property will be rejected.

PHASE I: The contractor shall deliver ADC architectures with detailed designs of critical pieces/blocks required for meeting the performance requirements, they shall deliver libraries with complete modeling & simulation results demonstrating the desired capabilities and requirements. The design should also target existing readily accessible IC processes. The contractor shall propose a plan for the manufacturing & testing of prototype hardware performance in electrical environments to be conducted in Phase II.

PHASE II: The contractor shall produce prototype hardware defined in Phase I, show met performance via laboratory testing, & deliver a formal assessment report including findings & discoveries for further technology

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advancement. Complete design libraries, macro ADC models, updated modeling & simulation results, prototype hardware, & final GDS shall be delivered at phase end. The contractor should coordinate their efforts with military GPS (e.g., MGUE) & specific platform (e.g. PGMs) receiver contractors.

PHASE III DUAL USE APPLICATIONS: Given successful completion of Phase II, the contractor shall work with military GPS and platform receiver contractors to implement, test, & demonstrate the technology in an RF front end that provides the best size, weight, power, and cost trade-off for the application spaces.

REFERENCES:1. Analog Devices, “Analog-Digital Conversion Handbook Third Edition”, Prentice Hall 1986.

2. H. Johnson and M. Graham, “High-Speed Digital Design”, Prentice Hall 1993.

3. M. Pelgrom, “Analog-to-Digital Conversion”, Springer 2010.

4. Jo et al, “RF front-end architecture for a triple-band CMOS GPS receiver,” Microelectronics Journal, Vol. 46, Issue 1, pp 27-35, January 2015.

KEYWORDS: Analog to digital converter; ADC; A/D Converters, microelectronics; integrated circuit design; GPS receiver, Navigation bands, GPS bands, L-band, MGUE

AF171-129 TITLE: Focal Plane Arrays (FPAs) for Coherent Ladar

TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Gail Nyikon, gail.nyikon@us.af.mil.

OBJECTIVE: Develop innovative fast framing small format FPAs needed for multi-function coherent sensors in the short wave infrared. Successful solutions will be low noise and compatible with space constrained airborne environments.

DESCRIPTION: Coherent imaging systems have the capability to provide high-resolution 3-D imagery for target identification at stand-off ranges. Coherent imaging methods which combine image synthesis and multi-wavelength 3-D imaging offer exciting possibilities for future imaging systems [1,2]. High bandwidth FPAs would not only allow these capabilities from an airborne platform, but would also enable additional modalities such as vibrometry [3]. An opportunity exists to reduce some of the conventional requirements for FPAs while extending their performance in factors relevant to coherent imaging. The innovative sensor would enable new holographic imaging techniques and may also lead to low volume, conformal active imaging systems. Possible commercial applications include diffuse correlation spectroscopy, speckle contrast imaging and others that would benefit from low noise high speed measurements.

Current state of the in frame rates for short-wave infrared (SWIR) FPAs is substantially less than 100kHz (even

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lower when not operated in a windowed mode), which is inadequate for the applications mentioned above [4]. FPAs with <100 noise equivalent photons and quantum efficiencies >0.8 are commonly available with simple thermoelectric cooling at 1.5 microns, but similar performance for detection at 2 microns typically requires more advanced cooling.

Systems designed to utilize coherent imaging modalities will require high frame rate FPAs, with a threshold of 250kHz, and an objective of 1MHz. The FPAs will be small format, with a threshold of 32 x 32 pixels and an objective of 64x64. The desired dynamic range is 8 bits, but can be traded with the array size and frame rate so that the total throughput is <10Gb/s. Due to the small format, high operability is critical (>99%).

Pixel pitches <40 microns with 100% fill factor and quantum efficiencies >0.7 are desired, where the quantum efficiency and the fill factor can be traded. A global shutter with minimum integration times on the order of 1 microsecond is needed, with dead times between frame integrations as low as 100ns. Detectors with less than 50 noise equivalent photons are strongly preferred, but higher noise counts are acceptable (<250) for solutions that extend the detector sensitivity to cover both 1.5 and 2 microns. However, the dynamic range should scale with the noise such that the full well depth of the detectors is roughly 8X the square of the noise equivalent photons.

Low SWAP designs (< 64 cubic in, < 2 kg) are preferred, and auxiliary requirements such as cooling should be considered in the system design. Solutions that do not need liquid cooling are strongly preferred. The FPA should be capable of external triggering and a communication protocol that compatible with an industry standard such as Camera Link is desirable.

No use of government materials, equipment, data, or facilities is anticipated.

PHASE I: The effectiveness of various candidate concepts will be evaluated. Preliminary designs will be modeled and fabrication feasibility of those designs will be evaluated. Shortcomings in fabrication and critical technology that would require additional development during Phase II will also be identified.

PHASE II: A prototype FPA will be developed and tested to verify key performance parameters.

PHASE III DUAL USE APPLICATIONS: FPA will be packaged for space constrained airborne environments, and inserted into larger overall sensor.

REFERENCES:1. J. Stafford, B. Duncan, and D. J. Rabb, "Range-compressed Holographic Aperture Ladar," in Imaging and Applied Optics 2015, OSA Technical Digest (online) (Optical Society of America, 2015), paper LM1F.3.

2. Stephen Crouch, Brant M. Kaylor, Zeb W. Barber, and Randy R. Reibel, "Three dimensional digital holographic aperture synthesis," Opt. Express 23, 23811-23816 (2015).

3. Brandon Redding, Allen Davis, Clay Kirkendall, and Anthony Dandridge, "Measuring vibrational motion in the presence of speckle using off-axis holography," Appl. Opt. 55, 1406-1411 (2016).

4. A. Rouvie et al., InGaAs Focal Plane Array developments and perspectives, Infrared Technology and Application XLI, Proc. of SPIE, Vol. 9451 (2015).

KEYWORDS: focal plane array, detector, ROIC, SWIR, LADAR, LIDAR, digital holography

AF171-130 TITLE: Small Unmanned Aircraft System (SUAS) 5-Inch Gimbal with Full Motion Video and Hyperspectral

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TECHNOLOGY AREA(S): Battlespace, Electronics, Sensors

OBJECTIVE: Develop a gimbal capable of collecting full motion video and hyperspectral measurements suitable for Small Unmanned Aircraft Systems (SUAS) platforms.

DESCRIPTION: SUAS are proliferating across the DoD. They fit into the USAF Intelligence, Surveillance, and Reconnaissance (ISR) strategy by providing local persistence, operation in contested environments, and low probability of detection. As the utility of SUAS is demonstrated, demands on their performance increases.

SUAS gimbal performance is typically limited to full color full motion video (FMV). The technology is limited to target detection and identification (det/ID) by image analysts and algorithms using spatial and color information alone. Hyperspectral imaging (HSI) sensors collect additional spectral information from scene imagery that can be used to detect and identify targets using spectral information alone. Combined hyperspectral data and FMV allows for improved det/ID performance through spatial and spectral processing. However, typical HSI systems are not appropriate for the cost, size, weight, and power (C-SWaP) requirements of SUASs.

This effort will provide a 5” diameter gimbal suitable for a Common Launch Tube-deployed SUAS of less than 50lbs operating at a typical slant range of 1500ft and altitude of 200 feet and higher. The gimbal shall provide full-color, NIIRS-6-quality (T) [NIIRS-7 or better (O)], visible-band images and full-color FMV with visible through near infrared (VNIR) hyperspectral measurements collected across the same field-of-view (FOV) as the FMV with roughly the same ground sample distance (T). The system should be able to operate in a staring mode. Note, due to the SWaP constraints, solutions may include point spectrometers that can be scanned to various parts of the FOV to collect spectral information from various objects in the scene based upon user/software cueing. The system shall provide the operator with situational awareness, target det/ID and tracking (T).

The gimbal FMV shall achieve at least NIIRS 6 (T) with desired NIIRS 7 or greater (O) performance. The spectrometer shall cover a visible-to-near infrared (VNIR) spectral range of 400-1000nm with 5nm spectral resolution (T) with an objective system including the shortwave infrared (SWIR) 1000-2500nm with 15nm spectral resolution (O). The FMV imagery shall be visually lossless after transmission (T). The transmitted chip/frame rate shall be 0.25 hertz (T), 2 hertz (O). Ground coverage of the FMV shall be sufficient to fully encompass the rear aspect of a vehicle (T), 20 x 20 feet (O) at range.

FMV and NIIRS 6 capability should be provided simultaneously (O). The FOVs shall be operator-steerable over a large part of a lower hemisphere field of regard (T). The imaging system(s) shall have the provision for non-uniformity correction (NUC), color balance, dynamic range, gamma, aperture and exposure control with no or limited operator intervention (T). The spectrometer system should be NUC-ed at a minimum (T) with preference to calibration to spectral radiance (O). The resulting data stream shall allow transmission over existing SUAS-capable encrypted digital data links (T). It is not expected that full spectral data cubes will be transmitted over data links, but rather detection cues and/or associated spectral signatures resulting from on-board real-time processing.

This effort will not develop entirely new gimbal structures, but will develop a payload, and processing capability. An off-the-shelf gimbal or mature prototype is the expected starting point. This gimbal shall support typical SUAS maneuvering and fly-ins, and shall compensate for disturbances due to gusts and air turbulence. The gimbal should provide accurate line-of-sight pointing data, on-gimbal inertial measurement, and interface to platform GPS (T).

PHASE I: Identify the hardware requirements for a NIIRS-6-capable 5” gimbal with spectrometer covering the solar reflective portion of the spectrum, including stabilization, optics, and focal plane array. Consider software approaches and algorithms as appropriate. Conduct a SRR. Prepare a preliminary design of the payload, identify existing 5" gimbal structures to use for the payload, and hold a PDR. Use modeling and simulation to justify performance.

PHASE II: Perform detailed design of the gimbal payload. Conduct Critical Design Review. Continue modeling and simulation to improve system performance. Based on these results, build and incorporate FMV + spectral payload into appropriate 5" gimbal. Provide all review board / safety of flight data required by USAF approval authorities.

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Conduct a Test Readiness Review. Evaluate gimbal performance in laboratory (T), tower (T), on a motion base (O) and flight test (O) environments. Flight test on contractor asset preferred. Use of government equipment and facilities for laboratory characterization and tower testing may be applicable for this effort but not required.

PHASE III DUAL USE APPLICATIONS: Refine design based on outcomes of tests and customer feedback in Phase II; develop a manufacturing plan and/or select a partner for production of 5” gimbals.

REFERENCES:1. Air Force Unmanned Aerial System (UAS) Flight Plan 2009-2047,http://archive.defense.gov/DODCMSShare/briefingslide/339/090723-D-6570C-001.pdf.

2. USAF Intelligence Targeting Guide,http://fas.org/irp/doddir/usaf/afpam14-210/part13.htm.

3. Tube-launched UAV:https://www.researchgate.net/publication/267377594_Design_of_a_Tube-Launched_UAV

4. Common Launch Tube:http://www.systima.com/

KEYWORDS: SUAS, Imaging, NIIRS, hyperspectral, compact, gimbal

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