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Contents

Proposal/Statement of Work

Timeline for NASA Student Launch .............................................................................................................. 2Design, Development, and Launch of a Reusable Rocket and Payload Statement of Work (SOW) ...................................................................................................... 3

Vehicle/Payload Criteria

Preliminary Design Review (PDR) Vehicle and Payload Experiment Criteria ............................................ 14Critical Design Review (CDR) Vehicle and Payload Experiment Criteria .................................................. 18Flight Readiness Review (FRR) Vehicle and Payload Experiment Criteria ............................................... 23Launch Readiness Review (LRR) Vehicle and Payload Experiment Criteria ............................................ 28Post Launch Assessment Review (PLAR) Vehicle and Payload Experiment Criteria ................................ 28Educational Engagement Form ................................................................................................................. 29NASA Project Life Cycle ............................................................................................................................ 31

Safety

High Power Rocket Safety Code ............................................................................................................... 44Minimum Distance Table ............................................................................................................................ 46Failures, Hazards and Risk ........................................................................................................................ 47Understanding Material Safety Data Sheets (MSDS) ................................................................................ 63

Awards

NASA Student Launch Awards................................................................................................................... 92

Proposal/ Statement of Work

Timeline for NASA Student Launch(Dates are subject to change.)

November 2013:8 Request for Proposal (RFP) goes out to all teams.22 Send electronic copy of completed proposal due by 8:00 a.m. Central Time to:

edward.m.jeffries@nasa.gov Jacobs ESSSA Group

and to

julie.d.clift@nasa.govNASA MSFC

26 Teamsnotifiedofselection

December 2013:3 Team teleconference Preliminary Design Review (PDR) Question and Answer Session 6 Web presence established for each team

January 2014:10 PDRreports,presentationslides,andflysheetpostedontheteamWebsiteby8:00a.m.CentralTime.13–17 PDR Presentations 23 Critical Design Review (CDR) Question and Answer Session

February 2014:28 CDRreports,presentationslides,andflysheetpostedontheteamWebsiteby8:00a.m.CentralTime.

March 2014:3–7 CDR Presentations 13 Flight Readiness Review (FRR) Question and Answer Session

April 2013:18 FRRreports,presentationslides,andflysheetpostedontheteamWebsiteby8:00a.m.CentralTime.21–25 Flight Readiness Review Presentations

May 2014:14 5:00 p.m.: All teams and team members arrive in Salt Lake City, Utah 5:30 p.m.: Team Lead meeting 6:30 p.m.: Launch Readiness Reviews (LRR) begin15–16 Launch Readiness Reviews17 Launch Day18 Backup Rain Day

June 2014:2 Post-Launch Assessment Review (PLAR) posted on the team Web site by 8:00 a.m. Central Time.13 Winning team announced.

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Design, Development, and Launch of a Reusable Rocket and Payload Statement of Work (SOW)

1. Project Name: NASA Student Launch

2. GoverningOffice:NASAMarshallSpaceFlightCenterAcademicAffairsOffice

3. Period of Performance: Eight (8) calendar months.

4. Introduction The NASA Student Launch is a research-based, competitive and experiential exploration project that provides

relevant and cost effective research and development to support the Space Launch System (SLS). Addition-ally, NASA Student Launch connects learners, educators and communities in NASA-unique opportunities that align with STEM Challenges under the NASA Education STEM Engagement line of business. NASA’s missions, discoveries, and assets provide opportunities for students that do not exist elsewhere. The proj-ect involves reaching a broad audience of colleges and universities across the nation in an 8-month commit-menttodesign,build,andflypayloadsorvehiclecomponentsthatsupportSLSonhighpowerrocketstoanaltitudedeterminedbytheRangeSafetyOfficerandeachteam’sresearchneeds.SupportedbytheHumanExploration and Operations (HEO) Mission Directorate and U.S. aerospace industry, NASA Student Launch is a NASA-conducted engineering design challenge to provide resources and experiences for students and fac-ulty that is built around a NASA mission, not textbook knowledge. Research/investigation topics are conceived bytheSLSProgramofficeincollaborationwithSLSindustrypartners.Researchresultswillbesharedbytheteams with NASA and utilized in future design/development of SLS and other projects.

After a competitive proposal selection process, teams participate in a series of design reviews that are sub-mitted to NASA via a team-developed website. These reviews mirror the NASA engineering design lifecycle, providing an experience that prepares students for the HEO workforce. Teams must complete a Prelimi-nary Design Review (PDR), Critical Design Review (CDR), Flight Readiness Review (FRR), Launch Readi-nessReview(LRR)thatincludesasafetybriefing,andanalyzepayloadandflightdataduringaPostLaunchAssessment Review (PLAR). Teams present their PDR, CDR, and FRR to a review panel of scientists, engi-neers,technicians,andeducatorsviaWebExtechnology.Reviewpanelmembers,theRangeSafetyOfficer(RSO),andSubjectMatterExperts(SME)providefeedbackandaskquestionsinordertoincreasethefidelitybetween the student payloads and HEO research needs, and score each team according to a standard scor-ing rubric.

The performance targets for the reusable launch vehicle and payload are

1. Vehicle Requirements1.1. The vehicle shall deliver the research payload to a predetermined altitude appropriate for the associ-

ated payload. 1.1.1. The target altitude shall not exceed 20,000 feet above ground level.1.1.2. ThefinaltargetaltitudewillbeapprovedbytheRangeSafetyOfficerandReviewPanelnolater

than PDR.

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1.2. Thevehicleshallcarryonecommerciallyavailable,barometricaltimeterforrecordingtheofficialaltitudeused in the competition scoring. Teams will be ranked according to the difference between the team’s targetaltitudeandtheactualaltitudeearnedduringtheofficiallaunch.Theteamwiththeleastvariancein target and actual altitudes will be ranked highest. The team with the largest variance will be ranked lowest. The highest rank will earn the full 100 points toward the altitude portion of the competition. The next highest rank will earn 97 out of the full 100 points, with each successive lower rank earning 3 points less than the next highest rank.1.2.1. Theofficialscoringaltimetershallreporttheofficialcompetitionaltitudeviaaseriesofbeepsto

becheckedafterthecompetitionflight.

1.2.2. Teams may have additional altimeters to control vehicle electronics and payload experiments.1.2.2.1. AttheLaunchReadinessReview,aNASAofficialwillmarkthealtimeterthatwillbe

usedfortheofficialscoring.1.2.2.2. Atthelaunchfield,aNASAofficialwillobtainthealtitudebylisteningtotheaudible

beepsreportedbytheofficialcompetition,markedaltimeter.1.2.2.3. Atthelaunchfield,toaidindeterminationofthevehicle’sapogee,allaudibleelec-

tronics,exceptfortheofficialaltitude-determiningaltimetershallbecapableofbeingturned off.

1.2.3. The following circumstances will warrant a score of zero for the altitude portion of the competi-tion:1.2.3.1. Theofficial,markedaltimeterisdamagedand/ordoesnotreportanaltitudeviaa

seriesofbeepsaftertheteam’scompetitionflight.1.2.3.2. TheteamdoesnotreporttotheNASAofficialdesignatedtorecordthealtitudewith

theirofficial,markedaltimeteronthedayofthelaunch.1.2.3.3. The altimeter reports an apogee altitude over 20,000 feet AGL.1.2.3.4. Therocketisnotflownatthecompetitionlaunchsite.

1.3. Thelaunchvehicleshallbedesignedtoberecoverableandreusable.Reusableisdefinedasbeingabletolaunchagainonthesamedaywithoutrepairsormodifications.

1.4. Thelaunchvehicleshallbecapableofbeingpreparedforflightatthelaunchsitewithin2hours,fromthetimetheFederalAviationAdministrationflightwaiveropens.

1.5. Thelaunchvehicleshallbecapableofremaininginlaunch-readyconfigurationatthepadforamini-mum of 1 hour without losing the functionality of any critical on-board component.

1.6. Thelaunchvehicleshallbecapableofbeinglaunchedbyastandard12voltdirectcurrentfiringsystem.ThefiringsystemwillbeprovidedbytheNASA-designatedRangeServicesProvider.

1.7. The launch vehicle shall require no external circuitry or special ground support equipment to initiate launch (other than what is provided by Range Services).

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1.8. The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchloratecompositepropellant(APCP)whichisapprovedandcertifiedbytheNationalAssociationof Rocketry (NAR), Tripoli Rocketry Association (TRA), and/or the Canadian Association of Rocketry (CAR).

1.9. Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria:1.9.1. The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating

Pressure) shall be 4:1 with supporting design documentation included in all milestone reviews.1.9.2. The low-cycle fatigue life shall be a minimum of 4:1.1.9.3. Each pressure vessel shall include a pressure relief valve that sees the full pressure of the

tank.1.9.4. Full pedigree of the tank shall be described, including the application for which the tank was

designed, and the history of the tank, including the number of pressure cycles put on the tank, by whom, and when.

1.10. AllteamsshallsuccessfullylaunchandrecovertheirfullscalerocketpriortoFRRinitsfinalflightcon-figuration.Thepurposeofthefullscaledemonstrationflightistodemonstratethelaunchvehicle’ssta-bility,structuralintegrity,recoverysystems,andtheteam’sabilitytopreparethelaunchvehicleforflight.Thefollowingcriteriamustbemetduringthefullscaledemonstrationflight:1.10.1. The vehicle and recovery system shall have functioned as designed.

1.10.2. Thepayloaddoesnothavetobeflownduringthefull-scaletestflight.Thefollowingrequire-ments still apply:1.10.2.1. Ifthepayloadisnotflown,masssimulatorsshallbeusedtosimulatethepayload

mass. 1.10.2.1.1. The mass simulators shall be located in the same approximate location

on the rocket as the missing payload mass.

1.10.2.2. If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle, those sys-temsshallbeactiveduringthefullscaledemonstrationflight.

1.10.3. Thefullscalemotordoesnothavetobeflownduringthefullscaletestflight.However,itis recommendedthatthefullscalemotorbeusedtodemonstratefullflightreadinessandaltitudeverification.Ifthefullscalemotorisnotflownduringthefullscaleflight,itisdesiredthatthemotorsimulate, as closely as possible, the predicted maximum velocity and maximum acceleration of thecompetitionflight.

1.10.4. Thevehicleshallbeflowninitsfullyballastedconfigurationduringthefullscaletestflight.Fullyballastedreferstothesameamountofballastthatwillbeflownduringthecompetitionflight.

1.10.5. Aftersuccessfullycompletingthefull-scaledemonstrationflight,thelaunchvehicleoranyofits componentsshallnotbemodifiedwithouttheconcurrenceoftheNASARangeSafetyOfficer(RSO).

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2. Recovery System Requirements2.1. The launch vehicle shall stage the deployment of its recovery devices, where a drogue parachute is

deployed at apogee and a main parachute is deployed at a much lower altitude. Tumble recovery or streamer recovery from apogee to main parachute deployment is also permissible, provided that kinetic energyduringdrogue-stagedescentisreasonable,asdeemedbytheRangeSafetyOfficer.

2.2. The parachute system(s) shall be designed and manufactured by the team. Commercially available parachute systems shall not be used on the vehicle.

2.3. At landing, each independent sections of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf.

2.4. The recovery system electrical circuits shall be completely independent of any payload electrical cir-cuits.

2.5. The recovery system shall contain redundant, commercially available altimeters. The term “altimeters” includesbothsimplealtimetersandmoresophisticatedflightcomputers.

2.6. Each altimeter shall be armed by a dedicated arming switch which is accessible from the exterior of the rocketairframewhentherocketisinthelaunchconfigurationonthelaunchpad.

2.7. Each altimeter shall have a dedicated power supply.

2.8. Each arming switch shall be capable of being locked in the ON position for launch.

2.9. Removable shear pins shall be used for both the main parachute compartment and the drogue para-chute compartment.

2.10. An electronic tracking device shall be installed in the launch vehicle and shall transmit the position of the tethered vehicle or any independent section to a ground receiver.2.10.1. Any rocket section, or payload component, which lands untethered to the launch vehicle shall

also carry an active electronic tracking device.2.10.2. Theelectronictrackingdeviceshallbefullyfunctionalduringtheofficialflightatthecompetition

launch site.

2.11. The recovery system electronics shall not be adversely affected by any other on-board electronic devicesduringflight(fromlaunchuntillanding).2.11.1. The recovery system altimeters shall be physically located in a separate compartment within

the vehicle from any other radio frequency transmitting device and/or magnetic wave producing device.

2.11.2. The recovery system electronics shall be shielded from all onboard transmitting devices, to avoid inadvertent excitation of the recovery system electronics.

2.11.3. The recovery system electronics shall be shielded from all onboard devices which may gener-ate magnetic waves (such as generators, solenoid valves, and Tesla coils) to avoid inadvertent excitation of the recovery system.

2.11.4. The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics.

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3. Payload Requirements3.1. Eachteamshalldesign,test,andflyapayloadpackagetosupportthedevelopmentofSLStechnology

which meets the following required criteria at a minimum:3.1.1. The payload shall incorporate a camera system that scans the surface during descent in order

to detect potential landing hazards.3.1.2. The data from the hazard detection camera shall be analyzed in real time by a custom

designed on-board software package that shall determine if landing hazards are present.3.1.3. The data from the surface hazard detection camera and software system shall be transmitted in

real time to a ground station.

3.2. Thepayloadshallbedesignedtoberecoverableandreusable.Reusableisdefinedasbeingabletobelaunchedagainonthesamedaywithoutrepairsormodifications.

3.3. Each team shall incorporate one payload option from each of the following columns in addition to the required payload from requirement 3.1.3.2.1.1. Research and analysis of solid propellant

rocket motors for in line and parallel staging.3.2.1.2. Liquid sloshing research in micrograv-

ity to support liquid propulsion system upgrades and development.

3.2.1.3. Structural and dynamic analysis of air-frame, propulsion, and electrical systems during boost.

3.2.1.4. Human and environmental studies under high acceleration to support Launch Abort System development.

3.2.1.5. Reduced Gravity Education Flight Program Option (see Requirement 3.4).

3.2.2.1. Payload fairing design and deployment mechanisms.

3.2.2.2. Aerodynamic analysis of structural protu-berances.

3.2.2.3. Studies of triboelectric charging and effect on vehicle subsystems.

3.2.2.4.Environmentaleffectsofsupersonicflighton vehicle paint/coatings.

3.4. NASA Student Launch is partnering with the NASA Reduced Gravity Education Flight Program (RGEFP)toofferachanceforoneteamtoflyamicrogravitypayloadonthereducedgravityaircraft.See the RGEFP website for more details: http://microgravityuniversity.jsc.nasa.gov/. The team chosen toparticipatewilldemonstratethehighestleveloffidelityinmeetingthefollowingrequirements:3.4.1. The team participating in NASA Student Launch may be of any size, but the team during the

RGEFPeventislimitedto6flyers(5prime,1alternate)and2groundcrewpersonnel.Teammembersshallbe18yearsorolderandUSCitizens.Eachflightcrewmembershallflyonce.

3.4.2. Student experiments shall be organized, designed, and operated by student team members alone.

3.4.3. ThepayloadshallbedesignedtoflyonaStudentLaunchrocket,yetbescalabletoflyontheRGEFP aircraft.

3.4.4. Payloads shall not involve human test subjects or invertebrate animals.3.4.5. Thepayloadshallbedesignedtoflytwiceonthereducedgravityaircraft.3.4.6. The payload on the RGEFP aircraft shall weigh no more than 200 pounds.3.4.7. The payload size limit on the RGEFP aircraft shall be no more than 24 in. by 60 in. by 60 in.3.4.8. Payloadexperimentsthatarefree-floating(notsecuredtotheaircraft)shallbenomorethan50

pounds and 24 in. on any side. 3.4.9. Theselectedteamshallcompleteamedicalquestionnaire,flightprogrampaperwork,Test

EquipmentDataPackagesixweekspriortotheflight,completetheTestReadinessReview,andspend8businessdaysinHouston,Texas,forflightweekactivities.

3.4.10. Foreignnationalswillnotbeabletoparticipateinflightweekactivities.

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4. General Requirements4.1. Eachteamshallusealaunchandsafetychecklist.ThefinalchecklistsshallbeincludedintheFRR

report and used during the Launch Readiness Review and launch day operations.

4.2. Students on the team shall do 100% of the project, including design, construction, written reports, pre-sentations,andflightpreparationwiththeexceptionofassemblingthemotorsandhandlingblackpow-der or any variant of ejection charges, or preparing and installing electric matches (to be done by the team’s mentor).

4.3. The team shall provide and maintain a project plan to include, but not limited to the following items: project milestones, budget and community support, checklists, personnel assigned, educational engagement events, and risks and mitigations.

4.4. Eachteamshallidentifya“mentor”whichisdefinedasanadultwhoisincludedasateammember,who will be supporting the team (or multiple teams) throughout the project year, and may or may not beaffiliatedwiththeschool,institution,ororganization.ThementorshallhavebeencertifiedbytheNational Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of thelaunchvehicle,andtherocketeershallhaveflownandsuccessfullyrecovered(usingelectronic,stagedrecovery)aminimumof2flightsinthisorahigherimpulseclass,priortoPDR.Thementorisdesignated as the individual owner of the rocket for liability purposes and must travel with the team to the launch at the competition launch site. One travel stipend will be provided per mentor regardless of the number of teams he or she supports. The stipend will only be provided if the team passes FRR and the team attends launch week in May.

4.5. The team shall identify all team members (exception Foreign National team members — see item 4.6) attending launch week activities by the Critical Design Review (CDR). Team members shall include: 4.5.1. Students actively engaged in the project throughout the entire year and currently enrolled in the

proposing institution.4.5.2. One mentor (see requirement 4.4). 4.5.3. No more than two adult educators.

4.6. ForeignNational(FN)teammembersshallbeidentifiedbythePreliminaryDesignReview(PDR) and may or may not have access to certain activities during launch week due to security restrictions. In addition, FN’s may be separated from their team during these activities.

4.7. Duringtestflights,teamsshallabidebytherulesandguidanceofthelocalrocketryclub’sRSO.Theallowanceofcertainvehicleconfigurationsand/orpayloadsattheNASAStudentLaunchcompetitionlaunchdoesnotgiveexplicitorimplicitauthorityforteamstoflythosecertainvehicleconfigurationsand/or payloads at other club launches. Teams should communicate their intentions to the local club’s Prefect and RSO before attending any NAR or TRA launch.

4.8. The team shall engage a minimum of 200 participants (at least 100 of those shall be middle school students or educators) in educational, hands-on science, technology, engineering, and mathematics (STEM)activities,asdefinedintheEducationalEngagementform,byFRR.Aneducationalengage-ment form shall be completed and submitted within two weeks after completion of an event. A sample of the educational engagement form can be found on page 29 of the handbook.

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4.9. The team shall develop and host a Web site for project documentation.4.9.1. Teams shall post, and make available for download, the required deliverables to the team Web

sitebytheduedatesspecifiedintheprojecttimeline.

At a minimum, the proposing team shall identify the following in a written proposal due to NASA MSFCbythedatesspecifiedintheprojecttimeline.

GeneralInformation–tobeincludedonthefirstpageoftheproposal.

1. Name of college or university, mailing address, and title of the project.

2. Listofselectedpayloadswithbriefdescriptionandrequirementnumbersidentified.

3. Name, title, and contact information for up to two adult educators.

4. Nameandtitleoftheindividualwhowilltakeresponsibilityforimplementationofthesafetyplan.(SafetyOfficer)

5. Name, title, and contact information for the student team leader.

6. Approximate number of student participants who will be committed to the project and their proposed duties. Includeanoutlineoftheprojectorganizationthatidentifiesthekeymanagers(studentsand/oreducatoradministrators)andthekeytechnicalpersonnel.Onlyusefirstnamesforidentifyingteammembers;donotincludesurnames.(Seerequirement4.5and4.6fordefinitionofteammembers)

7. Name of the NAR/TRA section(s) the team is associating with for launch assistance, mentor and review.

Facilities/Equipment1. Description of facilities and hours of accessibility, necessary personnel, equipment, and supplies that are

required to design and build a rocket and payload.

2. Computer Equipment: Describe the type of computer equipment accessible to the team for communications, designing, building and hosting a team Web site, and document development to support design reviews. The team shall provide and maintain a Web presence where the status of the project will be posted, as well as a list of needed materials and/or expertise. The team will provide the capability to communicate via e-mail on adailybasiswiththeNASAStudentLaunchOffice.Theinformationtechnologyidentifiedcouldincludecom-puter hardware, computer-aided drafting (CAD) system capability, Internet access, and e-mail capability.

The team shall provide additional computer equipment needed to perform video teleconferencing. Minimum requirements include the following:

� Windows, Mac, Linux, Unix, or Solaris computer systems. � Broadband internet connection. � Speakerphone capabilities in close proximity to the computer.

Cellular phones are not recommended for use as a speakerphone. � USB Webcam or analog video camera. � Personal name and contact information for connectivity issues.

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3. Teams must implement the Architectural and Transportation Barriers Compliance Board Electronic and Infor-mation Technology (EIT) Accessibility Standards (36 CFR Part 1194)

Subpart B-Technical Standards (http://www.section508.gov): � 1194.21 Software applications and operating systems. (a-l) � 1194.22 Web-based intranet and internet information and applications. 16 rules (a-p) � 1194.26 Desktop and portable computers. (a-d)

SafetyTheFederalAviationAdministration(FAA)[www.faa.gov]hasspecificlawsgoverningtheuseofairspace.Adem-onstration of the understanding and intent to abide by the applicable federal laws (especially as related to the use ofairspaceatthelaunchsitesandtheuseofcombustible/flammablematerial),safetycodes,guidelines,andpro-ceduresforbuilding,testing,andflyinglargemodelrocketsiscrucial.TheproceduresandsafetyregulationsoftheNAR[http://www.nar.org/safety.html]shouldbeusedforflightdesignandoperations.TheNAR/TRAmentorandSafetyOfficershalloverseelaunchoperationsandmotorhandling.

1. Provide a written safety plan addressing the safety of the materials used, facilities involved, and person responsible,i.e.,SafetyOfficer,forinsuringthattheplanisfollowed.Ariskassessmentshouldbedoneforalltheseaspectsinadditiontoproposedmitigations.Identificationofriskstothesuccessfulcompletionoftheproject should be included.

2. Provide a description of the procedures for NAR/TRA personnel to perform. Ensure the following: � Compliance with NAR high power safety code requirements [http://nar.org/NARhpsc.html]. � Performance of all hazardous materials handling and hazardous operations.

3. Describetheplanforbriefingstudentsonhazardrecognitionandaccidentavoidance,andconductingpre-launchbriefings.

4. Describe methods to include necessary caution statements in plans, procedures and other working docu-ments, including the use of proper Personal Protective Equipment.

5. Each team shall provide a plan for complying with federal, state, and local laws regarding unmanned rocket launchesandmotorhandling.Specifically,regardingtheuseofairspace,FederalAviationRegulations14CFR,SubchapterF,Part101,SubpartC;thehandlinganduseoflow-explosives(AmmoniumPerchlorateRocketMotors,APCP),CodeofFederalRegulation27Part55:CommerceinExplosives;andfireprevention,NFPA 1127 “Code for High Power Rocket Motors.”

6. Provide a plan for NRA/TRA mentor purchase, store, transport, and use rocket motors and energetic devices.

7. A written statement that all team members understand and will abide by the following safety regulations:a. Rangesafetyinspectionsofeachrocketbeforeitisflown.Eachteamshallcomplywiththedetermination

of the safety inspection or may be removed from the program.b. TheRangeSafetyOfficerhasthefinalsayonallrocketsafetyissues.Therefore,theRangeSafety

Officerhastherighttodenythelaunchofanyrocketforsafetyreasons.c. Any team that does not comply with the safety requirements will not be allowed to launch their rocket.

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Technical Design1. A proposed and detailed approach to rocket and payload design.

a. Includegeneralvehicledimensions,materialselectionandjustification,andconstructionmethods.b. Includeprojectedaltitudeandjustification.c. Include projected parachute system design and manufacturing process.d. Include projected motor type and size.e. Include projected payloads with hypothesis and/or stated goal for said payload.

● For teams pursuing the RGEFP payload option, include the following: ○ Address how the payload will be scaled up to take full advantage of the space available on the

microgravityflight. ○ Definetheresearcher’sinteractions/procedureswiththepayloadduringthemicrogravityflight. ○ Identify potential hazards or safety concerns and the associated mitigation plans.

f. Address the requirements for the vehicle, recovery system, and payload.g. Address major technical challenges and solutions.

Educational Engagement1. Include plans for required educational engagement activities (See requirement 4.8). Plans for measuring

event success shall be included.

Project Plan1. Provide a detailed development schedule/timeline covering all aspects necessary to successfully complete

the project.

2. Provide a detailed budget to cover all aspects necessary to successfully complete the project including team travel to launch.

3. Provide a detailed funding plan.

4. Provide a written plan for soliciting additional “community support,” which could include, but is not limited to, expertise needed, additional equipment/supplies, sponsorship, services (such as free shipping for launch vehicle components, if required, advertisement of the event, etc.), or partnering with industry or other public or private schools.

5. Address major programmatic challenges and solutions.

6. Develop a clear plan for sustainability of the rocket project in the local area. This plan should include how to provide and maintain established partnerships and regularly engage successive classes of students in rock-etry. It should also include partners (industry/community), recruitment of team members, funding sustainabil-ity, and educational engagement.

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Prior to award, all proposing entities may be required to brief NASA representatives. The time and the placeforthebriefingswillbedeterminedbytheNASAMSFCAcademicAffairsOffice.

Deliverables shall include:1. Areusablerocketandrequiredpayloadsystemsreadyfortheofficiallaunch.

2. Ascalemodeloftherocketdesignwithapayloadprototype.ThismodelshouldbeflownpriortotheCDR. AreportofthedatafromtheflightandthemodelshouldbebroughttotheCDR.

3. Reports, PowerPoint presentations, and Milestone Review Flysheets due according to the provided timeline, and shall be posted on the team Web site by the due date. (Dates are tentative at this point. Final dates will be announced at the time of award.)

4. Theteam(s)shallhaveaWebpresencenolaterthanthedatespecified.TheWebsiteshallbemaintained/updated throughout the period of performance.

5. Electronic copies of the Educational Engagement form(s) and lessons learned pertaining to the implemented educational engagement activities shall be submitted prior to the FRR and no later than two weeks after the educational engagement event.

The team shall participate in a PDR, CDR, FRR, LRR, and PLAR. (Dates are tentative and subject to change.)

The PDR, CDR, FRR, and LRR will be presented to NASA at a time and/or location to be determined byNASAMSFCAcademicAffairsOffice.

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Vehicle/PayloadCriteria

Preliminary Design Review (PDR)Vehicle and Payload Experiment Criteria

The PDR demonstrates that the overall preliminary design meets all requirements with acceptable risk, and within the cost and schedule constraints, and establishes the basis for proceeding with detailed design. Itshowsthatthecorrectdesignoptionshavebeenselected,interfaceshavebeenidentified,andverification methods have been described. Full baseline cost and schedules, as well as all risk assessment, management systems, and metrics, are presented.

The panel will be expecting a professional and polished report. It is advised to follow the order of sections as they appear below.

Preliminary Design Review Report

I) Summary of PDR report (1 page maximum)

Team Summary ● Team name and mailing address ● Location ● Nameofmentor,NAR/TRAnumberandcertificationlevel

Launch Vehicle Summary ● Size and mass ● Motor choice ● Recovery system ● Milestone Review Flysheet

Payload Summary ● Payload title and selected payloads with requirement number ● Summarize experiment

II) Changes made since Proposal (1-2 pages maximum)

Highlight all changes made since the proposal and the reason for those changes. ● Changes made to vehicle criteria ● Changes made to payload criteria ● Changes made to project plan

III) Vehicle Criteria

Selection,Design,andVerificationofLaunchVehicle ● Include a mission statement, requirements, and mission success criteria. ● Review the design at a system level, going through each system’s functional requirements (includes

sketches of options, selection rationale, selected concept, and characteristics). ● Describe the subsystems that are required to accomplish the overall mission. ● Describe the performance characteristics for the system and subsystems and determine the evaluation

andverificationmetrics.

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● Describetheverificationplananditsstatus.Ataminimum,atableshouldbeincludedthatlistseachrequirement(inSOW),andforeachrequirementbrieflydescribethedesignfeaturethatwillsatisfy thatrequirementandhowthatrequirementwillultimatelybeverified(suchasbyinspection,analysis, and/or test).

● Definetherisksandtheplansforreducingtherisksthroughanalysisortestingforeachsystem.Ariskplot that clearly portrays the risk mitigation schedule is highly encouraged. Take all factors that might affect the project including risks associated with testing, delivery of parts, adequate personnel, school holidays, budget costs, etc. Demonstrate an understanding of all components needed to complete the project and how risks/delays impact the project.

● Demonstrateplanningofmanufacturing,verification,integration,andoperations(includecomponent testing, functional testing, or static testing).

● Describetheconfidenceandmaturityofdesign. ● Include a dimensional drawing of entire assembly. The drawing set should include drawings of the entire

launch vehicle, compartments within the launch vehicle (such as parachute bays, payload bays, and elec-tronicsbays),andsignificantstructuraldesignfeaturesofthelaunchvehicle(suchasfinsandbulkheads).

● Include electrical schematics for the recovery system. ● Include a Mass Statement. Discuss the estimated mass of the launch vehicle, its subsystems, and com-

ponents. What is the basis of the mass estimate and how accurate is it? Discuss how much margin there isbeforethevehiclebecomestooheavytolaunchwiththeidentifiedpropulsionsystem.Areyouhold-ing any mass in reserve (i.e., are you planning for any mass growth as the design matures)? If so, how much? As a point of reference, a reasonable rule of thumb is that the mass of a new product will grow between25and33%betweenPDRandthedeliveryofthefinalproduct.

Recovery Subsystem ● Demonstrate that analysis has begun to determine size for mass, attachment scheme, deployment

process, and test results/plans with ejection charges and electronics. ● Discuss the major components of the recovery system (such as the parachutes, parachute harnesses,

attachment hardware, and bulkheads), and verify that they will be robust enough to withstand the expected loads.

Mission Performance Predictions ● State mission performance criteria. ● Showflightprofilesimulations,altitudepredictionswithsimulatedvehicledata,componentweights,and

simulated motor thrust curve, and verify that they are robust enough to withstand the expected loads. ● Show stability margin, simulated Center of Pressure (CP)/Center of Gravity (CG) relationship and locations. ● Calculate the kinetic energy at landing for each independent and tethered section of the launch vehicle. ● Calculatethedriftforeachindependentsectionofthelaunchvehiclefromthelaunchpadforfivedifferent

cases: no wind, 5-mph wind, 10-mph wind, 15-mph wind, and 20-mph wind.

Interfaces and Integration ● Describe payload integration plan with an understanding that the payload must be co-developed with

the vehicle, be compatible with stresses placed on the vehicle, and integrate easily and simply. ● Describe the interfaces that are internal to the launch vehicle, such as between compartments and

subsystems of the launch vehicle. ● Describe the interfaces between the launch vehicle and the ground (mechanical, electrical, and/or

wireless/transmitting). ● Describe the interfaces between the launch vehicle and the ground launch system.

Launch Operation Procedures ● Developachecklistoffinalassemblyandlaunchprocedures.

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Safety and Environment (Vehicle) ● Identifyasafetyofficerforyourteam. ● Provide a preliminary analysis of the failure modes of the proposed design of the rocket, payload integra-

tion, and launch operations, including proposed and completed mitigations. ● Provide a listing of personnel hazards and data demonstrating that safety hazards have been researched,

such as material safety data sheets, operator’s manuals, and NAR regulations, and that hazard mitigations have been addressed and enacted.

● Discuss any environmental concerns.

IV) Payload Criteria

Selection,Design,andVerificationofPayloadExperiment ● Review the design at a system level, going through each system’s functional requirements (includes

sketches of options, selection rationale, selected concept, and characteristics). ● Describe the payload subsystems that are required to accomplish the payload objectives. ● Describe the performance characteristics for the system and subsystems and determine the evaluation

andverificationmetrics. ● Describetheverificationplananditsstatus.Ataminimum,atableshouldbeincludedthatlistseach

payloadrequirementandforeachrequirementbrieflydescribethedesignfeaturethatwillsatisfythatrequirementandhowthatrequirementwillultimatelybeverified(suchasbyinspection,analysis, and/or test).

● Describe preliminary integration plan. ● Determine the precision of instrumentation, repeatability of measurement, and recovery system. ● Include drawings and electrical schematics for the key elements of the payload. ● Discuss the key components of the payload and how they will work together to achieve the desired

results for the experiment.

PayloadConceptFeaturesandDefinition ● Creativity and originality ● Uniquenessorsignificance ● Suitable level of challenge

Science Value ● Describe payload objectives. ● State the payload success criteria. ● Describe the experimental logic, approach, and method of investigation. ● Describe test and measurement, variables, and controls. ● Show relevance of expected data and accuracy/error analysis. ● Describe the preliminary experiment process procedures.

Safety and Environment (Payload) ● Identifysafetyofficerforyourteam. ● Provide a preliminary analysis of the failure modes of the proposed design of the rocket, payload

integration, and launch operations, including proposed and completed mitigations. ● Provide a listing of personnel hazards and data demonstrating that safety hazards have been researched,

such as material safety data sheets, operator’s manuals, and NAR regulations, and that hazard mitiga-tions have been addressed and enacted.

● Discuss any environmental concerns.

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V) Project Plan

Show status of activities and schedule ● Budget plan (in as much detail as possible) ● Funding plan ● Timeline (in as much detail as possible). GANTT charts are encouraged with a discussion of the

critical path. ● Educational engagement plan and status

VI) Conclusion

Preliminary Design Review Presentation

Please include the following in your presentation:

● Vehicledimensions,materials,andjustifications ● Static stability margin ● Planforvehiclesafetyverificationandtesting ● Baselinemotorselectionandjustification ● Thrust-to-weight ratio and rail exit velocity ● Launchvehicleverificationandtestplanoverview ● Drawing/Discussion of each major component and subsystem, especially the recovery subsystem ● Baseline payload design ● Payloadverificationandtestplanoverview

The PDR will be presented to a panel that may be comprised of any combination of scientists, engineers, safety experts, education specialists, and industry partners. This review should be viewed as the opportunity to convince the NASA Review Panel that the preliminary design will meet all requirements, has a high probability of meeting the mission objectives, and can be safely constructed, tested, launched, and recovered. Upon successful comple-tionofthePDR,theteamisgiventheauthoritytoproceedintothefinaldesignphaseofthelifecyclethatwill culminate in the Critical Design Review.

It is expected that the students deliver the report and answer all questions.

The presentation of the PDR shall be well prepared with a professional overall appearance. This includes, but isnotlimitedto,thefollowing:easy-to-seeslides;appropriateplacementofpictures,graphs,andvideos;profes-sionalappearanceofthepresenters;speakingclearlyandloudly;lookingintothecamera;referringtotheslides,notreadingthem;andcommunicatingtothepanelinanappropriateandprofessionalmanner.Theslidesshoulduse dark text on a light background.

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Critical Design Review (CDR)Vehicle and Payload Experiment Criteria

The CDR demonstrates that the maturity of the design is appropriate to support proceeding to full-scale fabrica-tion,assembly,integration,andtestandthatthetechnicaleffortisontracktocompletetheflightandground system development and mission operations in order to meet overall performance requirements within the iden-tifiedcostscheduleconstraints.Progressagainstmanagementplans,budget,andschedule,aswellasriskassessment,arepresented.TheCDRisareviewofthefinaldesignofthelaunchvehicleandpayloadsystem.All analyses should be complete and some critical testing should be complete. The CDR Report and Presentation should be independent of the PDR Report and Presentation. However, the CDR Report and Presentation may havethesamebasiccontentandstructureasthePDRdocuments,butwithfinaldesigninformationthatmayormay not have changed since PDR. Although there may be discussion of subscale models, the CDR documents aretoprimarilydiscussthefinaldesignofthefullscalelaunchvehicleandsubsystems.

The panel will be expecting a professional and polished report. It is advised to follow the order of sections as they appear below.

Critical Design Review Report

I) Summary of CDR report (1 page maximum)

Team Summary ● Team name and mailing address ● Location ● Nameofmentor,NAR/TRAnumberandcertificationlevel

Launch Vehicle Summary ● Size and mass ● Motor choice ● Recovery system ● Rail size ● Milestone Review Flysheet

Payload Summary ● Payload title and selected payloads with requirement number ● Summarize experiment

II) Changes made since PDR (1-2 pages maximum)

Highlight all changes made since PDR and the reason for those changes. ● Changes made to vehicle criteria ● Changes made to payload criteria ● Changes made to project plan

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III) Vehicle Criteria

DesignandVerificationofLaunchVehicleFlightReliabilityandConfidence

● Include mission statement, requirements, and mission success criteria ● Includemajormilestoneschedule(projectinitiation,design,manufacturing,verification,operations,

and major reviews) ● Review the design at a system level

○ Finaldrawingsandspecifications ○ Final analysis and model results, anchored to test data ○ Test description and results ○ Final motor selection

● Demonstrate that the design can meet all system level functional requirements. For each requirement, statethedesignfeaturethatsatisfiesthatrequirementandhowthatrequirementhasbeen,orwillbe,verified.

● Specify approach to workmanship as it relates to mission success. ● Discuss planned additional component, functional, or static testing. ● Status and plans of remaining manufacturing and assembly. ● Discuss the integrity of design.

○ Suitabilityofshapeandfinstyleformission ○ Properuseofmaterialsinfins,bulkheads,andstructuralelements ○ Proper assembly procedures, proper attachment and alignment of elements, solid connection

points, and load paths ○ Sufficientmotormountingandretention ○ Statusofverification ○ Drawings of the launch vehicle, subsystems, and major components ○ IncludeaMassStatement.Discusstheestimatedmassofthefinaldesignanditssubsystems

and components. Discuss the basis and accuracy of the mass estimate, the expected mass growthbetweenCDRandthedeliveryofthefinalproduct,andthesensitivityofthelaunchvehi-cle to mass growth (e.g., How much mass margin there is before the vehicle becomes too heavy to launch on the selected propulsion system?).

● Discuss the safety and failure analysis.

Subscale Flight Results ● Includeactualflightdatafromonboardcomputers,ifavailable. ● Comparethepredictedflightmodeltotheactualflightdata.Discusstheresults. ● Discusshowthesubscaleflightdatahasimpactedthedesignofthefull-scalelaunchvehicle.

Recovery Subsystem ● Describe the parachute, harnesses, bulkheads, and attachment hardware. ● Discuss the electrical components and how they will work together to safely recover the launch vehicle. ● Include drawings/sketches, block diagrams, and electrical schematics. ● Discussthekineticenergyatsignificantphasesofthemission,especiallyatlanding. ● Discuss test results. ● Discuss safety and failure analysis.

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Mission Performance Predictions ● State the mission performance criteria. ● Showflightprofilesimulations,altitudepredictionswithfinalvehicledesign,weights,andactualmotor

thrust curve. ● Show thoroughness and validity of analysis, drag assessment, and scale modeling results. ● Show stability margin and the actual CP and CG relationship and locations.

Payload IntegrationEase of integration

● Describe integration plan. ● Installationandremoval,interfacedimensions,andprecisionfit. ● Compatibility of elements. ● Simplicity of integration procedure.

Launch concerns and operation procedures ● Submitdraftoffinalassemblyandlaunchprocedures. ● Recovery preparation. ● Motor preparation. ● Igniter installation. ● Setup on launcher. ● Troubleshooting. ● Postflightinspection.

Safety and Environment (Vehicle) ● Identifysafetyofficerforyourteam. ● Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations, including proposed, and completed mitigations. ● Update the listing of personnel hazards and data demonstrating that safety hazards have been researched,

such as material safety data sheets, operator’s manuals, and NAR regulations, and that hazard mitigations have been addressed and enacted.

● Discuss any environmental concerns.

IV) Payload Criteria

TestingandDesignofPayloadExperiment ● Review the design at a system level.

○ Drawingsandspecifications ○ Analysis results ○ Test results ○ Integrity of design

● Demonstrate that the design can meet all system-level functional requirements. ● Specify approach to workmanship as it relates to mission success. ● Discuss planned component testing, functional testing, or static testing. ● Status and plans of remaining manufacturing and assembly. ● Describe integration plan. ● Discuss the precision of instrumentation and repeatability of measurement.

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● Discuss the payload electronics with special attention given to transmitters. ○ Drawings and schematics ○ Block diagrams ○ Batteries/power ○ Transmitter frequencies, wattage, and location ○ Test plans

● Provide a safety and failure analysis.

PayloadConceptFeaturesandDefinition ● Creativity and originality ● Uniquenessorsignificance ● Suitable level of challenge

Science Value ● Describe payload objectives. ● State the payload success criteria. ● Describe the experimental logic, approach, and method of investigation. ● Describe test and measurement, variables, and controls. ● Show relevance of expected data and accuracy/error analysis. ● Describe the experiment process procedures.

Safety and Environment (Payload) ● Identifysafetyofficerforyourteam. ● Update the preliminary analysis of the failure modes of the proposed design of the rocket and payload

integration and launch operations, including proposed and completed mitigations. ● Update the listing of personnel hazards, and data demonstrating that safety hazards have been

researched (such as material safety data sheets, operator’s manuals, NAR regulations), and that hazard mitigations have been addressed and mitigated.

● Discuss any environmental concerns.

V) Project Plan

Show status of activities and schedule ● Budget plan (in as much detail as possible) ● Funding plan ● Timeline (in as much detail as possible). GANTT charts are encouraged with a discussion of the

critical path. ● Educational engagement plan and status

VI) Conclusion

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Critical Design Review Presentation

Please include the following information in your presentation:

● Final launch vehicle dimensions ● Discuss key design features ● Final motor choice ● Rocketflightstabilityinstaticmargindiagram ● Thrust-to-weight ratio and rail exit velocity ● Mass Statement and mass margin ● Parachute sizes, recovery harness type, size, and length, and descent rates ● Kinetic energy at key phases of the mission, especially landing ● Predicted drift from the launch pad with 5-, 10-, 15-, and 20-mph wind ● Test plans and procedures ● Scalemodelflighttest ● Tests of the staged recovery system ● Final payload design overview ● Payload integration ● Interfaces (internal within the launch vehicle and external to the ground) ● Statusofrequirementsverification

The CDR will be presented to a panel that may be comprised of any combination of scientists, engineers, safety experts,educationspecialists,andindustrypartners.Theteamisexpectedtopresentanddefendthefinaldesignof the launch vehicle (including the payload), showing that design meets the mission objectives and requirements and that the design can be safety, constructed, tested, launched, and recovered. Upon successful completion of theCDR,theteamisgiventheauthoritytoproceedintotheconstructionandverificationphaseofthelifecyclewhich will culminate in a Flight Readiness Review.

It is expected that the students deliver the report and answer all questions.

The presentation of the CDR shall be well prepared with a professional overall appearance. This includes, but isnotlimitedto,thefollowing:easy-to-seeslides;appropriateplacementofpictures,graphs,andvideos;profes-sionalappearanceofthepresenters;speakingclearlyandloudly;lookingintothecamera;referringtotheslides,notreadingthem;andcommunicatingtothepanelinanappropriateandprofessionalmanner.Theslidesshouldbe made with dark text on a light background.

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Flight Readiness Review (FRR)Vehicle and Payload Experiment Criteria

The FRR examines tests, demonstrations, analyses, and audits that determine the overall system (all projects workingtogether)readinessforasafeandsuccessfulflight/launchandforsubsequentflightoperationsofthe as-builtrocketandpayloadsystem.Italsoensuresthatallflightandgroundhardware,software,personnel, and procedures are operationally ready.

The panel will be expecting a professional and polished report. It is advised to follow the order of sections as they appear below.

Flight Readiness Review Report

I) Summary of FRR report (1 page maximum)

Team Summary ● Team name and mailing address ● Location ● Nameofmentor,NAR/TRAnumberandcertificationlevel

Launch Vehicle Summary ● Size and mass ● Final motor choice ● Recovery system ● Rail size ● Milestone Review Flysheet

Payload Summary ● Payload title and selected payloads with requirement number ● Summarize experiment

II) Changes made since CDR (1-2 pages maximum)

Highlight all changes made since CDR and the reason for those changes. ● Changes made to vehicle criteria ● Changes made to payload criteria ● Changes made to project plan

III) Vehicle Criteria

Design and Construction of Vehicle ● Describe the design and construction of the launch vehicle, with special attention to the features that

will enable the vehicle to be launched and recovered safely. ○ Structuralelements(suchasairframe,fins,bulkheads,attachmenthardware,etc.). ○ Electrical elements (wiring, switches, battery retention, retention of avionics boards, etc.). ○ Drawings and schematics to describe the assembly of the vehicle.

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● Discussflightreliabilityconfidence.Demonstratethatthedesigncanmeetmissionsuccesscriteria. Discuss analysis, and component, functional, or static testing.

● Present test data and discuss analysis, and component, functional, or static testing of components and subsystems.

● Describe the workmanship that will enable mission success. ● Provide a safety and failure analysis, including a table with failure modes, causes, effects, and risk

mitigations. ● Discussfull-scalelaunchtestresults.Presentanddiscussactualflightdata.Compareandcontrastflight

data to the predictions from analysis and simulations. ● Provide a Mass Report and the basis for the reported masses.

Recovery Subsystem ● Describe and defend the robustness of as-built and as-tested recovery system.

○ Structural elements (such as bulkheads, harnesses, attachment hardware, etc.). ○ Electrical elements (such as altimeters/computers, switches, connectors). ○ Redundancy features. ○ Parachute sizes and descent rates ○ Drawings and schematics of the electrical and structural assemblies. ○ Rocket-locating transmitters with a discussion of frequency, wattage, and range. ○ Discuss the sensitivity of the recovery system to onboard devices that generate electromagnetic

fields(suchastransmitters).ThistopicshouldalsobeincludedintheSafetyandFailureAnalysissection.

● Suitable parachute size for mass, attachment scheme, deployment process, test results with ejection charge and electronics

● Safety and failure analysis. Include table with failure modes, causes, effects, and risk mitigations.

Mission Performance Predictions ● State mission performance criteria. ● Provideflightprofilesimulations,altitudepredictionswithrealvehicledata,componentweights,and

actual motor thrust curve. Include real values with optimized design for altitude. Include sensitivities. ● Thoroughness and validity of analysis, drag assessment, and scale modeling results. Compare analyses

andsimulationstomeasuredvaluesfromgroundand/orflighttests.Discusshowthepredictiveanalysesandsimulationhavebeenmademoreaccuratebytestandflightdata.

● Provide stability margin, with actual CP and CG relationship and locations. Include dimensional moment diagram or derivation of values with points indicated on vehicle. Include sensitivities.

● Discuss the management of kinetic energy through the various phases of the mission, with special atten-tion to landing.

● Discuss the altitude of the launch vehicle and the drift of each independent section of the launch vehicle for winds of 0-, 5-, 10-, 15-, and 20-mph.

Verification(Vehicle) ● Foreachrequirement(inSOW),describehowthatrequirementhasbeensatisfiedandbywhatmethod

therequirementwasverified.Note:Requirementsareoftensatisfiedbydesignfeaturesofaproduct,andrequirementsareusuallyverifiedbyoneormoreofthefollowingmethods:analysis,inspection,andtest.

● Theverificationstatementforeachrequirementshouldincluderesultsoftheanalysis,inspection, and/ortestwhichprovethattherequirementhasbeenproperlyverified.

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Safety and Environment (Vehicle) ● Provide a safety and mission assurance analysis. Provide a Failure Modes and Effects Analysis (which

can be as simple as a table of failure modes, causes, effects, and mitigations/controls put in place to minimize the occurrence or effect of the hazard or failure). Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur and/or worst consequences).

● As the program is moving into the operational phase of the Life Cycle, update the listing of personnel hazards, including data demonstrating that safety hazards that will still exist after FRR. Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible.

● Discuss any environmental concerns that remain as the project moves into the operational phase of the life cycle.

Payload Integration ● Describe the integration of the payload into the launch vehicle. ● Demonstratecompatibilityofelementsandshowfitatinterfacedimensions. ● Describe and justify payload-housing integrity. ● Demonstrate integration: show a diagram of components and assembly with documented process.

IV) Payload Criteria

ExperimentConceptThis concerns the quality of science. Give clear, concise, and descriptive explanations.

● Creativity and originality ● Uniquenessorsignificance

Science Value ● Describe science payload objectives in a concise and distinct manner. ● State the mission success criteria. ● Describetheexperimentallogic,scientificapproach,andmethodofinvestigation. ● Explain how it is a meaningful test and measurement, and explain variables and controls. ● Discuss the relevance of expected data, along with an accuracy/error analysis, including tables and plots. ● Provide detailed experiment process procedures.

Payload Design ● Describe the design and construction of the payload and demonstrate that the design meets all mission

requirements. ○ Structural elements (such as airframe, bulkheads, attachment hardware, etc.). ○ Electrical elements (wiring, switches, battery retention, retention of avionics boards, etc.). ○ Drawings and schematics to describe the design and assembly of the payload.

● Provide information regarding the precision of instrumentation and repeatability of measurement (include calibration with uncertainty).

● Provideflightperformancepredictions(flightvaluesintegratedwithdetailedexperimentoperations). ● Specify approach to workmanship as it relates to mission success. ● Discussthetestandverificationprogram.

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Verification ● Foreachpayloadrequirement,describehowthatrequirementhasbeensatisfied,andbywhatmethod

therequirementwasverified.Note:Requirementsareoftensatisfiedbydesignfeatures,andrequire-mentsareusuallyverifiedbyoneormoreofthefollowingmethods:analysis,inspection,andtest.

● Theverificationstatementforeachpayloadrequirementshouldincluderesultsoftheanalysis,inspection,and/ortestwhichprovethattherequirementhasbeenproperlyverified.

Safety and Environment (Payload)This will describe all concerns, research, and solutions to safety issues related to the payload.

● Provide a safety and mission assurance analysis. Provide a Failure Modes and Effects Analysis (which can be as simple as a table of failure modes, causes, effects, and mitigations/controls put in place to minimize the occurrence or effect of the hazard or failure). Discuss likelihood and potential consequences for the top 5 to 10 failures (most likely to occur and/or worst consequences).

● As the program is moving into the operational phase of the Life Cycle, update the listing of personnel hazards, including data demonstrating that safety hazards that will still exist after FRR. Include a table which discusses the remaining hazards and the controls that have been put in place to minimize those safety hazards to the greatest extent possible.

● Discuss any environmental concerns that still exist.

V) Launch Operations Procedures

ChecklistProvide detailed procedure and check lists for the following (as a minimum).

● Recovery preparation ● Motor preparation ● Igniter installation ● Setup on launcher ● Launch procedure ● Troubleshooting ● Postflightinspection

Safety and Quality AssuranceProvide detailed safety procedures for each of the categories in the Launch Operations Procedures checklist. Include the following:

● Provide data demonstrating that risks are at acceptable levels. ● Provide risk assessment for the launch operations, including proposed and completed mitigations. ● Discuss environmental concerns. ● Identify individual that is responsible for maintaining safety, quality and procedures checklists.

VI) Project Plan

Show status of activities and schedule ● Budget plan (in as much detail as possible) ● Funding plan ● Timeline (in as much detail as possible). GANTT charts are encouraged with a discussion of the

critical path. ● Educational engagement plan and status

VII) Conclusion

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Flight Readiness Review Presentation

Please include the following information in your presentation:

● Launch Vehicle design and dimensions ● Discuss key design features of the launch vehicle ● Motor description ● Rocketflightstabilityinstaticmargindiagram ● Launch thrust-to-weight ratio and rail exit velocity ● Mass statement ● Parachute sizes and descent rates ● Kinetic energy at key phases of the mission, especially at landing ● Predicted altitude of the launch vehicle with a 5-, 10-, 15-, and 20-mph wind ● Predicted drift from the launch pad with a 5-, 10-, 15-, and 20-mph wind ● Test plans and procedures ● Full-scaleflighttest.Presentanddiscusstheactualflighttestdata. ● Recovery system tests ● SummaryofRequirementsVerification(launchvehicle) ● Payload design and dimensions ● Key design features of the launch vehicle ● Payload integration ● Interfaces with ground systems ● Summaryofrequirementsverification(payload)

The FRR will be presented to a panel that may be comprised of any combination of scientists, engineers, safety experts, education specialists, and industry partners. The team is expected to present and defend the as-built launch vehicle (including the payload), showing that the launch vehicle meets all requirements and mission objec-tives and that the design can be safely launched and recovered. Upon successful completion of the FRR, the team is given the authority to proceed into the Launch and Operational phases of the life cycle.

It is expected that the students deliver the report and answer all questions.

The presentation of the FRR shall be well prepared with a professional overall appearance. This includes, but isnotlimitedto,thefollowing:easytoseeslides;appropriateplacementofpictures,graphs,andvideos;profes-sionalappearanceofthepresenters;speakingclearlyandloudly;lookingintothecamera;referringtotheslides,notreadingthem;andcommunicatingtothepanelinanappropriateandprofessionalmanner.Theslidesshouldbe made with dark text on a light background.

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Launch Readiness Review (LRR)Vehicle and Payload Experiment Criteria

The Launch Readiness Review (LRR) will be held by NASA and the National Association of Rocketry (NAR), our launch services provider. These inspections are only open to team members and mentors. These names were submitted as part of your team list. All rockets/payload will undergo a detailed, deconstructive, hands-on inspec-tion. Your team should bring all components of the rocket and payload except for the motor, black powder, and e-matches.Beabletopresent:anchoredflightpredictions,anchoreddriftpredictions(15mphcrosswind),proce-dures and checklists, and Cp and Cg with loaded motor marked on the airframe. The rockets will be assessed for structural, electrical integrity, and safety features. At a minimum, all teams should have:

● Anairframepreparedforflightwiththeexceptionofenergeticmaterials. ● Datafromthepreviousflight. ● Alistofanyflightanomaliesthatoccurredonthepreviousfullscaleflightandthemitigationactions. ● Alistofanychangestotheairframesincethelastflight. ● Flight simulations. ● Pre-flightchecklistandFlySheet.

A“punchlist”willbegeneratedforeachteam.Itemsidentifiedonthepunchlistshouldbecorrectedandverifiedby NAR/NASA on Friday evening. Teams will not be assigned a time on Friday evening, but should come to the hoteltohavetheseitemsapproved.Aflightcardwillbeprovidedtoteams,shouldbecompleted,andprovided at the RSO booth on launch day.

Post-Launch Assessment Review (PLAR)Vehicle and Payload Experiment Criteria

ThePLARisanassessmentofsystemin-flightperformance.

Your PLAR should include the following items at a minimum. Your PLAR should be about 4-15 pages in length. ● Team name ● Motor used ● Brief payload description ● Rocket height ● Rocket diameter ● Rocket mass ● Altitude reached (Feet) ● Vehicle Summary ● Data analysis & results of vehicle ● Payload summary ● Data analysis & results of payload ● Scientificvalue ● Visual data observed ● Lessons learned ● Summary of overall experience (what you attempted to do versus the results and how you felt your results

were;howvaluableyoufelttheexperiencewas) ● Educational Engagement summary ● Budget Summary

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Educational Engagement Form

Please  complete  and submit this form each time  you host an educational engagement event.(Return  within 2 weeks of the event end date)

School/Organization name:

Date(s) of event:

Location of event:

Instructions for  participant  count

Education/Direct Interactions: A count of participants in instructional,  hands-­‐on  activities where participants engage in  learning  STEM topic by actively participating  in  a activity. This includes instructor-­‐ led facilitation around an activity regardless of

media (e.g. DLN, face-­‐to-­‐face, downlink.etc.). Example: Students learn  about Newton’s Laws through building  an flying  arocket. This type of interaction will  count towards your requirement for the  project.

Education/Indirect Interactions:   A count of participants engaged in learning a STEM topic through instructor-­‐led facilitation orpresentation. Example: Students learn  about Newton’s Laws through   PowerPoint presentation.

Outreach/Direct Interaction: A count of participants who do not necessarily learn a STEM topic, but are able to get a hands-­‐on  look at STEM hardware.   For example, team does a presentation to students about their Student Launch project, brings theirrocket  and components to the event, and flies a rocket  at  the end of  the presentation.

Outreach/Indirect Interaction: A count of participants that interact with the team. For example: The team sets up a display atthe local museum during Science Night. Students come by an talk to  the team about their project.

Grade level and number of participants: (If  you are able to break down the participants into  grade levels: PreK-­‐4, 5-­‐9,  10-­‐12, an 12+, this will be helpful.)

Education OutreachParticipant’sGrade Level Indirect Indirect

Direct Interactions Direct InteractionsInteractions InteractionsK-­‐45-­‐910-­‐1212+Educators (5-­‐9)Educators (other)

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Are the participants with  a special group/organization  (i.e. Girl Scouts, 4-­‐H, school)? Y N

If yes, what group/organization?

Briefly describe your activities with  this group:

Did you conduct an evaluation? If so, what were the results?

Describe how you measured the success of the event.

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le, J

uly

2012

32

P

lan

for t

he d

esig

n, b

uild

, ver

ifica

tion,

flig

ht o

pera

tions

, and

di

spos

al o

f the

des

ired

syst

em

M

aint

ain

cons

iste

ncy

betw

een

proj

ects

Set

exp

ecta

tions

for P

roje

ct M

anag

ers,

Sci

entis

ts, &

Eng

inee

rs

◦Pl

ans

and

Del

iver

able

s◦

Fide

lity

◦Ti

min

g

NA

SA

Pro

ject

Life

Cyc

le, J

uly

2012

33

Ref

eren

ce:

NP

R 7

120.

5D, F

igur

e 2-

4: “

The

NA

SA P

roje

ct L

ife C

ycle

” N

AS

A P

roje

ct L

ife C

ycle

, Jul

y 20

12

34

Phas

e A

Acqu

isiti

on &

Re

quire

men

ts

Phas

e B

Prel

imin

ary

Des

ign

Phas

e C

Fina

l Des

ign

Phas

e D

Fa

bric

atio

n &

Laun

ch

Phas

e E

Ope

ratio

ns &

Su

stai

nmen

t

Phas

e F

Dis

posa

l

Auth

ority

to P

roce

ed

SRR

PDR

CDR

FRR La

unch

PL

AR

•AT

P (A

utho

rity

to P

roce

ed) –

Fun

ding

is a

pplie

d to

the

cont

ract

/effo

rt an

d w

ork

perfo

rman

ce c

an b

egin

•S

RR

(Sys

tem

Req

uire

men

ts R

evie

w) –

Top

Lev

el R

equi

rem

ents

are

con

verte

d in

to s

yste

m re

quire

men

ts.

Sys

tem

Req

uire

men

ts a

re re

view

ed a

nd a

utho

rity

is g

iven

to p

roce

ed in

to P

relim

inar

y D

esig

n. T

he N

AS

AS

tude

nt L

aunc

h sk

ips

this

ste

p. N

ote:

Thi

s re

view

is s

kipp

ed, d

ue to

tim

e co

nstra

ints

.•

PD

R (P

relim

inar

y D

esig

n R

evie

w) –

Pre

limin

ary

Des

ign

is re

view

ed a

nd a

utho

rity

is g

iven

to p

roce

ed in

to F

inal

Des

ign.

•C

DR

(Crit

ical

Des

ign

Rev

iew

) – F

inal

Des

ign

is re

view

ed a

nd a

utho

rity

is g

iven

to p

roce

ed to

bui

ld th

e sy

stem

.•

FRR

(Flig

ht R

eadi

ness

Rev

iew

) – A

s-bu

ilt d

esig

n an

d te

st d

ata

are

revi

ewed

and

aut

horit

y is

giv

en fo

r Lau

nch.

•P

LAR

(Pos

t Lau

nch

Ass

essm

ent R

epor

t) -

Sum

mar

ize

proj

ect (

crad

le to

gra

ve),

disc

uss

mis

sion

resu

lts a

ndco

mpa

re to

exp

ecte

d re

sults

, doc

umen

t les

sons

lear

ned.

NAS

A Pr

ojec

t Life

Cyc

le, J

uly

2012

35

O

bjec

tive

◦Pr

ove

the

feas

ibilit

y to

bui

ld a

nd la

unch

the

rock

et/p

aylo

ad d

esig

n.◦

Prov

e th

at a

ll sy

stem

requ

irem

ents

will

be m

et.

◦R

ecei

ve a

utho

rity

to p

roce

ed to

the

Fina

l Des

ign

Phas

e

Typi

cal P

rodu

cts

(Veh

icle

and

Pay

load

) ◦

Prel

imin

ary

Des

ign

Dis

cuss

ion

D

raw

ings

, ske

tche

s

Iden

tific

atio

n an

d di

scus

sion

of c

ompo

nent

s

Anal

yses

(suc

h as

Veh

icle

Tra

ject

ory

Pred

ictio

ns) a

nd S

imul

atio

n R

esul

ts

R

isks

Mas

s St

atem

ent a

nd M

ass

Mar

gin

◦Sc

hedu

le fr

om P

DR

to L

aunc

h (in

clud

ing

desi

gn, b

uild

, tes

t)◦

Cos

t/Bud

get S

tate

men

t◦

Mis

sion

Pro

file

(Con

cept

of O

pera

tions

)◦

Inte

rface

s (w

ithin

the

syst

em a

nd e

xter

nal t

o th

e sy

stem

)◦

Test

and

Ver

ifica

tion

Plan

(for

sat

isfy

ing

requ

irem

ents

)◦

Gro

und

Supp

ort E

quip

men

t Des

igns

/Iden

tific

atio

n◦

Safe

ty F

eatu

res

NA

SA

Pro

ject

Life

Cyc

le, J

uly

2012

36

O

bjec

tive

◦C

ompl

ete

the

final

des

ign

of th

e ro

cket

/pay

load

sys

tem

◦R

ecei

ve a

utho

rity

to p

roce

ed in

to F

abric

atio

n an

d Ve

rific

atio

n ph

ase

In

a p

erfe

ct w

orld

, fab

ricat

ion/

proc

urem

ent

of th

e fin

al s

yste

m w

ould

n’t b

egin

unt

il a

succ

essf

ul c

ompl

etio

n of

CD

R.

D

ue to

sch

edul

e co

nstra

ints

, how

ever

, it i

s of

ten

nece

ssar

y to

sta

rt pr

ocur

emen

ts a

nd

fabr

icat

ion

prio

r to

CD

R.

Pr

ocur

emen

ts a

nd F

abric

atio

n th

at s

tart

prio

r to

CD

R a

dd a

n ex

tra r

isk

to th

e Pr

ojec

t be

caus

e de

sign

issu

es m

ay b

e di

scov

ered

at C

DR

that

impa

ct p

rocu

rem

ents

or

fabr

icat

ion.

Ty

pica

l Pro

duct

s (V

ehic

le a

nd P

aylo

ad)

◦PD

R D

eliv

erab

les

(mat

ured

to re

flect

the

final

des

ign)

◦R

epor

t and

dis

cuss

com

plet

ed te

sts

◦Pr

oced

ures

and

Che

cklis

ts

NA

SA

Pro

ject

Life

Cyc

le, J

uly

2012

37

O

bjec

tive

◦Pr

ove

that

the

Roc

ket/P

aylo

ad S

yste

m h

as b

een

fully

bui

lt, te

sted

, and

ver

ified

tom

eet t

he s

yste

m re

quire

men

ts◦

Prov

e th

at a

ll sy

stem

requ

irem

ents

hav

e be

en, o

r will

be,

met

◦R

ecei

ve a

utho

rity

to p

roce

ed to

Lau

nch

Ty

pica

l Pro

duct

s (V

ehic

le a

nd P

aylo

ad)

◦Sc

hedu

le◦

Cos

t Sta

tem

ent

◦D

esig

n O

verv

iew

Ke

y co

mpo

nent

s

Key

draw

ings

and

layo

uts

Tr

ajec

tory

and

oth

er k

ey a

naly

ses

Ke

y Sa

fety

Fea

ture

s

Mas

s St

atem

ent

R

emai

ning

Ris

ks

◦M

issi

on P

rofil

e◦

Pres

enta

tion

and

anal

ysis

and

mod

els

(use

real

test

dat

a)◦

Syst

em R

equi

rem

ents

Ver

ifica

tion

◦G

roun

d Su

ppor

t Equ

ipm

ent

◦Pr

oced

ures

and

Che

ck L

ists

NA

SA

Pro

ject

Life

Cyc

le, J

uly

2012

38

O

bjec

tive

◦To

per

form

a h

ands

-on

final

insp

ectio

n of

the

rock

et s

yste

m, p

rior t

o la

unch

◦P

erfo

rmed

by

the

oper

ator

s of

the

Laun

ch R

ange

Pr

oces

s ◦

Roc

kets

dec

onst

ruct

ed

Mec

hani

cal c

ompo

nent

s pu

lled

and

twis

ted

E

lect

roni

cs a

nd W

iring

insp

ecte

d (a

s m

uch

as p

ossi

ble)

Rec

over

y S

yste

m f

ully

insp

ecte

d ◦

Que

stio

ns a

sked

A

rmin

g, A

ctiv

atio

n, E

xecu

tion

Seq

uenc

es

R

ocke

t an

d P

aylo

ad F

unct

ions

◦

Laun

ch D

ay P

roce

dure

s re

view

ed◦

Que

stio

ns A

nsw

ered

(any

thin

g ab

out L

aunc

h D

ay o

r Ran

ge O

pera

tions

)◦

Act

ions

giv

en to

repa

ir un

safe

ele

men

ts in

the

rock

et s

yste

m (i

f any

are

foun

d)

N

ote:

Thi

s in

spec

tion

is a

Pre

Ran

ge S

afet

y O

ffice

r (R

SO) i

nspe

ctio

n.

◦It

occu

rs o

ne d

ay b

efor

e la

unch

and

it p

urpo

se is

to g

ive

the

Stu

dent

Tea

ms

an o

ppor

tuni

ty to

cor

rect

hard

war

e is

sues

that

cou

ld o

ther

wis

e re

sult

in th

e de

nial

of l

aunc

h of

thei

r roc

ket.

◦A

final

RS

O in

spec

tion

will

occ

ur a

t the

laun

ch s

ite (j

ust l

ike

a no

rmal

NA

R/T

RA

RS

O In

spec

tion

at th

ela

unch

site

).

NA

SA

Pro

ject

Life

Cyc

le, J

uly

2012

39

S

umm

ary

of th

e P

roje

ct

S

umm

ary

of th

e Ve

hicl

e an

d P

aylo

ad

◦Es

peci

ally

not

e an

ythi

ng th

at c

hang

ed a

fter F

RR

P

rese

ntat

ion

of V

ehic

le a

nd P

aylo

ad R

esul

ts

◦C

ompa

rison

to p

redi

cted

resu

lts◦

Dis

cuss

ion

of a

nom

alie

s

Less

ons

Lear

ned

NA

SA

Pro

ject

Life

Cyc

le, J

uly

2012

40

ww

w.n

asa.

gov

41

Safety

High Power Rocket Safety CodeProvided by the National Association of Rocketry

1. Certification.Iwillonlyflyhighpowerrocketsorpossesshighpowerrocketmotorsthatarewithinthescopeofmyusercertificationandrequiredlicensing.

2. Materials.Iwilluseonlylightweightmaterialssuchaspaper,wood,rubber,plastic,fiberglass,orwhennecessary ductile metal, for the construction of my rocket.

3. Motors.Iwilluseonlycertified,commerciallymaderocketmotors,andwillnottamperwiththesemotorsor use them for any purposes except those recommended by the manufacturer. I will not allow smoking, openflames,norheatsourceswithin25feetofthesemotors.

4. Ignition System. I will launch my rockets with an electrical launch system, and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area. My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch, and will use a launch switch that returns to the “off” position when released. If my rocket has onboard ignition systems for motors or recovery devices, these will have safety interlocks that interrupt the current path until the rocket is at the launch pad.

5. Misfires. If my rocket does not launch when I press the button of my electrical launch system, I will remove the launcher’s safety interlock or disconnect its battery, and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket.

6. Launch Safety. I will use a 5-second countdown before launch. I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table, and that a means is available to warn participants and spectators in the event of a problem. I will check the stability of my rocket before flightandwillnotflyitifitcannotbedeterminedtobestable.

7. Launcher. I will launch my rocket from a stable device that provides rigid guidance until the rocket has attainedaspeedthatensuresastableflight,andthatispointedtowithin20degreesofvertical.Ifthewind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocitybeforeseparationfromthelauncher.Iwilluseablastdeflectortopreventthemotor’sexhaustfrom hitting the ground. I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table, and will increase this distance by a factor of 1.5 if the rocket motor being launched uses titanium sponge in the propellant.

8. Size. My rocket will not contain any combination of motors that total more than 40,960 N-sec (9208 pound-seconds)oftotalimpulse.Myrocketwillnotweighmoreatliftoffthanone-thirdofthecertifiedaverage thrust of the high power rocket motor(s) intended to be ignited at launch.

9. Flight Safety. I will not launch my rocket at targets, into clouds, near airplanes, nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site, and will not put anyflammableorexplosivepayloadinmyrocket.Iwillnotlaunchmyrocketsifwindspeedsexceed 20milesperhour.IwillcomplywithFederalAviationAdministrationairspaceregulationswhenflying, and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site.

44

10. Launch Site. I will launch my rocket outdoors, in an open area where trees, power lines, buildings, and persons not involved in the launch do not present a hazard, and that is at least as large on its smallest dimensionasone-halfofthemaximumaltitudetowhichrocketsareallowedtobeflownatthatsiteor1500 feet, whichever is greater.

11. Launcher Location. My launcher will be at least one half the minimum launch site dimension, or 1500 feet(whicheverisgreater)fromanyinhabitedbuilding,orfromanypublichighwayonwhichtrafficflowexceeds10vehiclesperhour,notincludingtrafficflowrelatedtothelaunch.Itwillalsobenocloserthanthe appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site.

12. Recovery System. I will use a recovery system such as a parachute in my rocket so that all parts of myrocketreturnsafelyandundamagedandcanbeflownagain,andIwilluseonlyflame-resistantorfireproofrecoverysystemwaddinginmyrocket.

13. Recovery Safety. I will not attempt to recover my rocket from power lines, tall trees, or other dangerous places,flyitunderconditionswhereitislikelytorecoverinspectatorareasoroutsidethelaunchsite,norattempt to catch it as it approaches the ground.

45

Minimum Distance Table

Installed Total Impulse (Newton-

Seconds)

Equivalent High Power Motor

Type

Minimum Diameter of

Cleared Area (ft.)

Minimum Personnel Distance (ft.)

Minimum Personnel Distance (ComplexRocket)(ft.)

0 – 320.00 H or smaller 50 100 200

320.01 – 640.00 I 50 100 200

640.01 – 1,280.00 J 50 100 200

1,280.01 – 2,560.00

K 75 200 300

2,560.01 – 5,120.00

L 100 300 500

5,120.01 – 10,240.00

M 125 500 1000

10,240.01 – 20,480.00

N 125 1000 1500

20,480.01 – 40,960.00

O 125 1500 2000

Note:AComplexrocketisonethatismulti-stagedorthatispropelledbytwoormorerocketmotors Revision of July 2008 Provided by the National Association of Rocketry (www.nar.org)

46

Nat

iona

l Aer

onau

tics

and

Spac

e Ad

min

istra

tion

Failu

res,

Haz

ards

and

Ris

k

How

to Id

entif

y, T

rack

and

M

itiga

te

ww

w.n

asa.

gov

47

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Exa

mpl

es fr

om H

ome

G

ettin

g to

wor

k on

tim

e (“

mis

sion

suc

cess

”)

R

isks

: wea

ther

, tra

ffic

jam

, ala

rm d

oesn

’t rin

g

How

do

we

plan

for t

hese

risk

s?

Fa

ilure

: the

car

doe

sn’t

star

t

How

do

we

try to

mak

e su

re th

at it

will

star

t?

H

azar

d: b

ad ro

ads,

oth

er d

river

s, s

udde

n ch

ange

s in

traf

fic fl

ow

H

ow d

o w

e pl

an fo

r thi

s an

d av

oid

prob

lem

s?

G

ettin

g to

wor

k on

tim

e m

eans

that

we

have

reco

gniz

ed

the

risks

, fai

lure

mod

es, a

nd h

azar

ds, a

nd h

ave

take

n ac

tion

to re

duce

thei

r pro

babi

lity

and

impa

ct.

This

sam

e ap

proa

ch im

prov

es th

e pr

obab

ility

of s

ucce

ss

for a

pro

ject

.

48

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Ris

k D

efin

ition

Th

e co

mbi

natio

n of

the

prob

abili

ty o

f an

unde

sire

d ev

ent a

nd th

e co

nseq

uenc

es, i

mpa

ct,

or s

ever

ity o

f the

eve

nt.

R

isk

asse

ssm

ent i

nclu

des

Wha

t can

go

wro

ng

H

ow li

kely

is it

to o

ccur

Wha

t the

con

sequ

ence

s ar

e

Ris

k M

itiga

tion

is

Ap

plic

atio

n of

met

hods

to le

ssen

the

prob

abilit

y an

d/or

impa

ct o

f the

und

esire

d ev

ent

49

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Exa

mpl

es o

f Ris

k

Plan

ned

desi

gn w

ill b

e ov

er b

udge

t

Key

pers

onne

l will

leav

e th

e pr

ogra

m

U

nava

ilabi

lity

of e

quip

men

t whe

n ne

eded

to

supp

ort s

ched

ule

St

uden

ts h

ave

man

y ot

her d

eman

ds o

n tim

e an

d do

not

hav

e tim

e to

fini

sh th

e pr

ojec

t

Parts

una

vaila

bilit

y

Mis

haps

Com

mun

icat

ion

issu

es

Ba

d w

eath

er o

n la

unch

day

50

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Ris

k M

anag

emen

t

“Ris

k m

anag

emen

t is

a co

ntin

uous

pro

cess

that

iden

tifie

s ris

ks;

an

alyz

es th

eir i

mpa

ct a

nd p

riorit

izes

them

;

deve

lops

and

car

ries

out p

lans

for r

isk

miti

gatio

n or

acc

epta

nce;

track

s ris

ks a

nd th

e im

plem

enta

tion

of m

itiga

tion

plan

s;

su

ppor

ts in

form

ed, t

imel

y, a

nd e

ffect

ive

deci

sion

s to

con

trol r

isks

an

d m

itiga

tion

plan

s;

an

d as

sure

s th

at ri

sk in

form

atio

n is

com

mun

icat

ed a

nd

docu

men

ted.

Ris

k m

anag

emen

t is

driv

en b

y es

tabl

ishe

d su

cces

s cr

iteria

and

is

per

form

ed b

y th

e w

hole

team

”

(fr

om N

AS

A P

rogr

am a

nd P

roje

ct M

anag

emen

t Pro

cess

es a

nd R

equi

rem

ents

)

51

Failu

res,

Haz

ards

, and

Pre

vent

ion,

Jul

y 20

12

Exa

mpl

es o

f Tab

les

to In

clud

e in

P

DR

, CD

R, F

RR

R

isk

Prob

abili

ty I

mpa

ct

Miti

gatio

n P

roje

ct fa

lls b

ehin

d sc

hedu

le d

ue to

m

ultip

le d

eman

ds o

n tim

e

Hig

hly

prob

able

La

te d

eliv

ery

of P

DR

, C

DR

, FR

R;

inco

mpl

ete

proj

ect

Cre

ate

a sc

hedu

le

with

mar

gin

for

prob

lem

s, tr

ack

prog

ress

; div

ide

wor

k am

ong

team

Par

ts a

re u

nava

ilabl

e P

roba

bilit

y is

low

La

st m

inut

e de

sign

ch

ange

s H

ave

desi

gn o

ptio

ns

and

mul

tiple

sou

rces

; fin

aliz

e de

sign

and

or

der p

arts

ear

ly

Key

per

sonn

el le

ave

proj

ect

Pro

babi

lity

is lo

w

Ext

ra w

ork

for

mem

bers

; lat

e de

liver

y; in

com

plet

e pr

ojec

t

Hav

e pr

imar

y an

d ba

ckup

ass

ignm

ents

; do

cum

ent a

ctiv

ities

; co

mm

unic

ate

Pro

ject

is o

ver

budg

et

Hig

hly

prob

able

La

st m

inut

e de

sign

ch

ange

s fo

r cos

t cu

tting

; inc

ompl

ete

proj

ect

Trac

k pr

ogre

ss; h

ave

mul

tiple

fund

ing

sour

ces

52

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Failu

res

D

urin

g th

e ro

cket

des

ign

proc

ess,

eac

h co

mpo

nent

and

sys

tem

sho

uld

be a

naly

zed

for

failu

re m

odes

:

How

can

it fa

il

Wha

t are

the

cons

eque

nces

of t

he fa

ilure

How

can

the

failu

re b

e pr

even

ted

Th

is in

clud

es s

yste

m in

tegr

atio

n an

d gr

ound

su

ppor

t equ

ipm

ent,

as w

ell a

s th

e ro

cket

and

pa

yloa

d

Doc

umen

t the

ana

lysi

s an

d up

date

as

nece

ssar

y

53

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Failu

re E

xam

ples

P

arac

hute

s fa

il to

dep

loy

Fa

ilure

to ig

nite

Uns

tabl

e fli

ght

Fa

ilure

to c

olle

ct d

ata

P

ower

loss

54

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Exa

mpl

es o

f Tab

les

to In

clud

e in

P

DR

, CD

R, F

RR

Fa

ilure

Mod

es a

nd E

ffec

ts A

naly

sis o

f Pro

pulsi

on S

yste

mPr

opul

sion

Tea

m: D

anie

l Chh

itt, J

ason

Bac

k

Func

tion

Pote

ntia

l Fai

lure

Mod

ePo

tent

ial E

ffect

s of F

ailu

reFa

ilure

Pre

vent

ion

1Pr

opel

lant

fails

to ig

nite

.To

tal m

issi

on fa

ilure

, roc

ket

does

not

take

off

.Pr

oper

igni

tion

syst

em

setu

p.

2Pr

opel

lant

igni

tes b

ut

extin

guis

hes b

efor

e de

sire

d bu

rn ti

me.

Roc

ket m

ay n

ot re

ach

desi

red

heig

ht, p

aylo

ad fa

ilure

.Pr

oper

mot

or a

nd p

rope

llant

in

spec

tion

and

test

ing.

3M

otor

mou

ntin

g fa

ils a

nd

mot

or la

unch

es th

roug

h th

e ro

cket

.

Poss

ible

des

truct

ion

of a

ll sy

stem

s; a

vion

ics,

reco

very

, pa

yloa

d

Prop

er m

otor

mou

ntin

g st

ruct

ure

and

load

test

ing

of

mou

ntin

g st

ruct

ure.

4Pr

opel

lant

igni

tes b

ut c

ause

s a

cata

stro

phic

exp

losi

on.

Poss

ible

des

truct

ion

of a

ll sy

stem

s; a

vion

ics,

reco

very

, pa

yloa

d, st

ruct

ure.

Prop

er m

otor

and

pro

pella

nt

insp

ectio

n an

d te

stin

g.

5Pr

opel

lant

igni

tes b

ut b

urns

th

roug

h m

otor

cas

ing.

Seve

re lo

ss o

f sta

bilit

y, p

ossi

ble

dest

ruct

ion

of a

ll sy

stem

s.Pr

oper

test

ing

of m

otor

ca

sing

and

pro

pella

nt.

6M

otor

cas

ing

beco

mes

de

tach

ed d

urin

g fli

ght.

Roc

ket m

ay n

ot re

ach

desi

red

heig

ht, m

otor

bec

omes

a

proj

ectil

e.

Prop

er te

stin

g an

d m

ount

ing

of m

otor

cas

ing

to th

e st

ruct

ure.

55

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Haz

ards

Th

e pr

ojec

t can

be

done

saf

ely

and

succ

essf

ully

, but

a fe

w h

azar

ds m

ust b

e cl

early

reco

gniz

ed, u

nder

stoo

d, a

nd

miti

gate

d.

S

afet

y of

the

stud

ents

is N

AS

A’s

firs

t pr

iorit

y an

d m

ust n

ever

be

com

prom

ised

.

Ther

e ar

e m

any

reso

urce

s av

aila

ble

to

help

with

this

con

cern

.

56

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Haz

ard

Exa

mpl

es

A

dhes

ives

, sol

vent

s, a

nd p

aint

Bla

ck P

owde

r and

sol

id p

rope

llant

Use

of T

ools

Laun

ch s

ite fa

ilure

s

Pre

ssur

ized

/col

d hy

brid

sys

tem

s

Oth

er h

azar

ds a

ssoc

iate

d w

ith a

par

ticul

ar

desi

gn

57

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Saf

ety

Res

ourc

es a

nd M

etho

ds

N

AR S

afet

y C

odes

and

Men

tors

NAR

cer

tific

atio

ns a

nd tr

aini

ng

M

ater

ial S

afet

y D

ata

Shee

ts

O

pera

tors

Man

uals

Dev

elop

men

t and

adh

eren

ce to

ass

embl

y an

d la

unch

pr

oced

ures

Equi

pmen

t, su

ch a

s go

ggle

s, g

love

s, s

turd

y sh

oes,

har

d ha

ts, c

otto

n cl

othi

ng, f

ire e

xtin

guis

hers

Envi

ronm

ent,

such

as

good

ven

tilat

ion,

rest

rictin

g ce

ll ph

ones

aro

und

elec

tric

mat

ches

Plan

ning

and

com

mun

icat

ion;

des

igna

te s

omeo

ne

resp

onsi

ble

to lo

ok a

t act

iviti

es fr

om a

saf

ety

pers

pect

ive

U

se th

e bu

ddy

syst

em

58

Failu

res,

Haz

ards

, and

Pre

vent

ion,

Jul

y 20

12

Exa

mpl

es o

f Tab

les

to In

clud

e in

P

DR

, CD

R, F

RR

H

azar

d Ef

fect

of H

azar

d M

itiga

tion

Che

mic

als

in p

aint

, sol

vent

, ad

hesi

ve

Pos

sibl

e re

spira

tory

and

ski

n irr

itatio

n R

ead

MS

DS

for p

reca

utio

ns;

wea

r glo

ves;

hav

e go

od

vent

ilatio

n

Igni

tion

of b

lack

pow

der o

r oth

er

pyro

tech

nic

or e

xplo

sive

co

mpo

unds

Fire

, dam

age

to e

quip

men

t, pe

rson

al in

jury

Fo

llow

saf

ety

rule

s; w

ear c

otto

n cl

othi

ng; d

o no

t sm

oke

or h

ave

othe

r sta

tic o

r spa

rk p

rodu

cing

ite

ms

in th

e ar

ea

Use

of p

ower

tool

s C

uts

or o

ther

inju

ries,

dam

age

to e

quip

men

t, fly

ing

debr

is

Follo

w m

anuf

actu

rer’s

saf

ety

inst

ruct

ions

; wea

r gog

gles

; do

not o

pera

te w

ithou

t sup

ervi

sion

Mis

fire,

han

gfire

on

laun

ch p

ad

Roc

ket m

ay n

ot b

e sa

fe to

ap

proa

ch

Writ

e pr

oced

ures

to p

lan

for t

his

cont

inge

ncy

and

follo

w; b

e pa

tient

and

wai

t; co

nsul

t with

ex

perts

59

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

Mis

sion

Suc

cess

M

issi

on S

ucce

ss is

the

resu

lt of

atte

ntio

n to

det

ail,

and

a th

orou

gh, h

ones

t as

sess

men

t of r

isks

, fai

lure

mod

es a

nd

haza

rds.

Failu

re is

ofte

n th

e be

st te

ache

r, so

pla

n to

te

st a

s m

uch

as p

ossi

ble.

Team

wor

k an

d co

mm

unic

atio

n ar

e es

sent

ial f

or a

suc

cess

ful p

roje

ct.

60

Failu

res,

Haz

ards

, and

Ris

k, J

uly

2012

ww

w.n

asa.

gov

61

Und

erst

andi

ng M

SD

S’s

By: J

eff M

itche

ll M

SFC

Env

ironm

enta

l Hea

lth

Nat

iona

l Aer

onau

tics

and

Spa

ce A

dmin

istra

tion

ww

w.n

asa.

gov

63

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Wha

t is

an M

SD

S?

•A

Mat

eria

l Saf

ety

Dat

a Sh

eet

(MSD

S) is

a d

ocum

ent

prod

uced

by

a m

anuf

actu

rer o

f apa

rticu

lar c

hem

ical

and

isin

tend

ed to

giv

e a

com

preh

ensi

ve o

verv

iew

of h

owto

saf

ely

wor

k w

ith o

r han

dle

this

chem

ical

64

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Wha

t is

an M

SD

S?

•M

SDS’

s do

not

hav

e a

stan

dard

form

at,

but t

hey

are

all r

equi

red

to h

ave

certa

inin

form

atio

n pe

r OSH

A 29

CFR

191

0.12

00•

Man

ufac

ture

rs o

f che

mic

als

fulfi

ll th

ere

quire

men

ts o

f thi

s O

SHA

stan

dard

indi

ffere

nt w

ays

65

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Req

uire

d da

ta fo

r MS

DS

’s

•Id

entit

y of

haz

ardo

us c

hem

ical

•

Che

mic

al a

nd c

omm

on n

ames

•

Phys

ical

and

che

mic

al c

hara

cter

istic

s •

Phys

ical

haz

ards

•

Hea

lth h

azar

ds

•R

oute

s of

ent

ry

•Ex

posu

re li

mits

66

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Req

uire

d da

ta fo

r MS

DS

’s (C

ont.)

•C

arci

noge

nici

ty•

Proc

edur

es fo

r saf

e ha

ndlin

g an

d us

e•

Con

trol m

easu

res

•Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

•D

ate

of la

st M

SDS

upda

te•

Man

ufac

ture

r’s n

ame,

add

ress

, and

pho

nenu

mbe

r

67

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12 Im

porta

nt A

genc

ies

•AC

GIH

–Th

e A

mer

ican

Con

fere

nce

of G

over

nmen

tal

Indu

stria

l Hyg

ieni

st d

evel

op a

nd p

ublis

hoc

cupa

tiona

l exp

osur

e lim

its fo

r man

ych

emic

als,

thes

e lim

its a

re c

alle

d TL

V’s

(Thr

esho

ld L

imit

Valu

es)

68

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Impo

rtant

Age

ncie

s (C

ont.)

•AN

SI–

The

Am

eric

an N

atio

nal S

tand

ards

Inst

itute

isa

priv

ate

orga

niza

tion

that

iden

tifie

s in

dust

rial

and

publ

ic n

atio

nal c

onse

nsus

sta

ndar

ds th

atre

late

to s

afe

desi

gn a

nd p

erfo

rman

ce o

feq

uipm

ent a

nd p

ract

ices

69

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Impo

rtant

Age

ncie

s (C

ont.)

•N

FPA

–Th

e N

atio

nal F

ire P

rote

ctio

n A

ssoc

iatio

n,am

ong

othe

r thi

ngs,

est

ablis

hed

a ra

ting

syst

em u

sed

on m

any

labe

ls o

f haz

ardo

usch

emic

als

calle

d th

e N

FPA

Dia

mon

d–

The

NFP

A D

iam

ond

give

s co

ncis

ein

form

atio

n on

the

Hea

lth h

azar

d,Fl

amm

abilit

y ha

zard

, Rea

ctiv

ity h

azar

d, a

ndS

peci

al p

reca

utio

ns–

An

exam

ple

of th

e N

FPA

Dia

mon

d is

on

the

next

slid

e

70

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

NFP

A D

iam

ond

71

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Impo

rtant

Age

ncie

s (C

ont.)

•N

IOSH

–Th

e N

atio

nal I

nstit

ute

of O

ccup

atio

nal S

afet

yan

d H

ealth

is a

n ag

ency

of t

he P

ublic

Hea

lthS

ervi

ce th

at te

sts

and

certi

fies

resp

irato

ry a

ndai

r sam

plin

g de

vice

s. I

t als

o in

vest

igat

esin

cide

nts

and

rese

arch

es o

ccup

atio

nal s

afet

y

72

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Impo

rtant

Age

ncie

s (C

ont.)

•O

SHA

–Th

e O

ccup

atio

nal S

afet

y an

d H

ealth

Adm

inis

tratio

n is

a F

eder

al A

genc

y w

ith th

em

issi

on to

mak

e su

re th

at th

e sa

fety

and

heal

th c

once

rns

of a

ll A

mer

ican

wor

kers

are

bein

g m

et

73

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Exp

osur

e Li

mits

•O

ccup

atio

nal e

xpos

ure

limits

are

set

by

diffe

rent

age

ncie

s•

Occ

upat

iona

l exp

osur

e lim

its a

re d

esig

ned

to re

flect

a s

afe

leve

l of e

xpos

ure

•Pe

rson

nel e

xpos

ure

abov

e th

e ex

posu

relim

its is

not

con

side

red

safe

74

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Exp

osur

e Li

mits

(Con

t.)

•O

SHA

calls

thei

r exp

osur

e lim

its, P

EL’s

,w

hich

sta

nds

for P

erm

issi

ble

Expo

sure

Lim

it–

OS

HA

PE

L’s

rare

ly c

hang

e•

ACG

IH, e

stab

lishe

s TL

V’s,

whi

ch s

tand

sfo

r Thr

esho

ld L

imit

Valu

es–

AC

GIH

TLV

’s a

re u

pdat

ed a

nnua

lly

75

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Exp

osur

e Li

mits

(Con

t.)

•A

Cei

ling

limit

(not

ed b

y C

) is

aco

ncen

tratio

n th

at s

hall

neve

r be

exce

eded

at a

ny ti

me

•An

IDLH

atm

osph

ere

is o

ne w

here

the

conc

entra

tion

of a

che

mic

al is

hig

h en

ough

that

it m

ay b

e Im

med

iate

ly D

ange

rous

toLi

fe a

nd H

ealth

76

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Exp

osur

e Li

mits

(Con

t.)

•A

STE

L, is

a S

hort

Term

Exp

osur

e Li

mit

and

is u

sed

to re

flect

a 1

5 m

inut

eex

posu

re ti

me

•A

TWA,

is a

Tim

e W

eigh

ted

Aver

age

and

isus

ed to

refle

ct a

n 8

hour

exp

osur

e tim

e

77

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Che

mic

al a

nd P

hysi

cal P

rope

rties

•

Boilin

g Po

int

–Th

e te

mpe

ratu

re a

t whi

ch th

e ch

emic

al c

hang

es fr

om li

quid

pha

se to

vapo

r pha

se•

Mel

ting

Poin

t–

The

tem

pera

ture

at w

hich

the

chem

ical

cha

nges

from

sol

id p

hase

toliq

uid

phas

e•

Vapo

r Pre

ssur

e–

The

pres

sure

of a

vap

or in

equ

ilibr

ium

with

its

non-

vapo

r pha

ses.

Mos

tof

ten

the

term

is u

sed

to d

escr

ibe

a liq

uid’

s te

nden

cy to

eva

pora

te•

Vapo

r Den

sity

–Th

is is

use

d to

hel

p de

term

ine

if th

e va

por w

ill ri

se o

r fal

l in

air

•Vi

scos

ity–

It is

com

mon

ly p

erce

ived

as

"thic

knes

s", o

r res

ista

nce

to p

ourin

g. A

high

er v

isco

sity

equ

als

a th

icke

r liq

uid

78

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Che

mic

al a

nd P

hysi

cal P

rope

rties

(C

ont.)

•Sp

ecifi

c G

ravi

ty–

This

is u

sed

to h

elp

dete

rmin

e if

the

liqui

d w

ill fl

oat o

r sin

k in

wat

er•

Solu

bilit

y–

This

is th

e am

ount

of a

sol

ute

that

will

dis

solv

e in

a s

peci

fic s

olve

ntun

der g

iven

con

ditio

ns•

Odo

r thr

esho

ld–

The

low

est c

once

ntra

tion

at w

hich

mos

t peo

ple

may

sm

ell t

he c

hem

ical

•Fl

ash

poin

t–

The

low

est t

empe

ratu

re a

t whi

ch th

e ch

emic

al c

an fo

rm a

n ig

nita

ble

mix

ture

with

air

•U

pper

(UEL

) and

low

er e

xplo

sive

lim

its (L

EL)

–At

con

cent

ratio

ns in

air

belo

w th

e LE

L th

ere

is n

ot e

noug

h fu

el to

cont

inue

an

expl

osio

n; a

t con

cent

ratio

ns a

bove

the

UEL

the

fuel

has

disp

lace

d so

muc

h ai

r tha

t the

re is

not

eno

ugh

oxyg

en to

beg

in a

reac

tion

79

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Thin

gs y

ou s

houl

d le

arn

from

MS

DS

’s

•Is

this

che

mic

al h

azar

dous

?–

Rea

d th

e H

ealth

Haz

ard

sect

ion

•W

hat w

ill ha

ppen

if I

am e

xpos

ed?

–Th

ere

is u

sual

ly a

sec

tion

calle

d S

ympt

oms

ofE

xpos

ure

unde

r Hea

lth H

azar

d•

Wha

t sho

uld

I do

if I a

m o

vere

xpos

ed?

–R

ead

Em

erge

ncy

and

Firs

t-aid

pro

cedu

res

•H

ow c

an I

prot

ect m

ysel

f fro

m e

xpos

ure?

–R

ead

Rou

tes

of E

ntry

, Pro

cedu

res

for s

afe

hand

ling

and

use,

and

Con

trol m

easu

res

80

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

Take

you

r tim

e!

•Si

nce

MSD

S’s

don’

t hav

e a

stan

dard

form

at, w

hat y

ou a

re s

eeki

ng m

ay n

ot b

ein

the

first

pla

ce y

ou lo

ok•

Stud

y yo

ur M

SDS’

s be

fore

ther

e is

apr

oble

m s

o yo

u ar

en’t

rush

ed•

Rea

d th

e en

tire

MSD

S, b

ecau

sein

form

atio

n in

one

loca

tion

may

com

plim

ent i

nfor

mat

ion

in a

noth

er

81

The

follo

win

g sl

ides

are

an

abb

revi

ated

ver

sion

of

a re

al M

SD

S

Stud

y it

and

beco

me

mor

e fa

mili

ar w

ith th

is c

hem

ical

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

82

MSD

S:

METH

YL E

TH

YL K

ETO

NE

SECTIO

N 1

. CH

EM

ICAL P

RO

DU

CT A

ND

CO

MPAN

Y I

DEN

TIF

ICATIO

N

MD

L I

NFO

RM

ATIO

N S

YSTEM

S,

INC.

14600 C

ATALIN

A S

TREET

1-8

00-6

35-0

064 O

R

1-5

10-8

95-1

313

FO

R E

MERG

EN

CY S

OU

RCE I

NFO

RM

ATIO

N

CO

NTACT:

1-6

15-3

66-2

000 U

SA

CAS N

UM

BER:

78-9

3-3

RTECS N

UM

BER:

EL6475000

EU

NU

MBER (

EIN

ECS):

201-1

59-0

EU

IN

DEX N

UM

BER:

606-0

02-0

0-3

SU

BSTAN

CE:

METH

YL E

TH

YL K

ETO

NE

TRAD

E N

AM

ES/S

YN

ON

YM

S:

BU

TAN

ON

E;

2-B

UTAN

ON

E;

ETH

YL M

ETH

YL K

ETO

NE;

METH

YL A

CETO

NE;

3-B

UTAN

ON

E;

MEK;

SCO

TCH

-GRIP

® B

RAN

D S

OLV

EN

T #

3 (

3M

); S

TO

P, S

HIE

LD

, PEEL R

ED

UCER (

PYRAM

ID

PLA

STIC

S,

INC.)

; STABO

ND

C-T

HIN

NER (

STABO

ND

CO

RP.

); O

ATEY C

LEAN

ER (

OATEY

CO

MPAN

Y);

RCRA U

159;

UN

1193;

STCC 4

909243;

C4H

8O

; O

HS14460

CH

EM

ICAL F

AM

ILY:

Keto

nes,

alip

hatic

CREATIO

N D

ATE:

Sep 2

8 1

984

REVIS

ION

DATE:

Mar

30 1

997

Abbre

via

ted M

SD

S

Manufa

cture

r nam

e

and p

hone #

Last

revis

ion

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

83

SECTIO

N 2

. CO

MPO

SIT

ION

, IN

FO

RM

ATIO

N O

N I

NG

RED

IEN

TS

CO

MPO

NEN

T:

METH

YL E

TH

YL K

ETO

NE

CAS N

UM

BER:

78-9

3-3

PERCEN

TAG

E:

100

SECTIO

N 3

. H

AZARD

S ID

EN

TIF

ICATIO

N

NFPA R

ATIN

GS (

SCALE 0

-4):

Health=

2

Fire=

3

React

ivity=

0

2 3 0

EM

ERG

EN

CY O

VERVIE

W:

CO

LO

R:

colo

rless

PH

YSIC

AL F

ORM

: liq

uid

O

DO

R:

min

ty, sw

eet

odor

MAJO

R H

EALT

H H

AZARD

S:

resp

irato

ry t

ract

irr

itation,

skin

irr

itation,

eye

irrita

tion,

centr

al nerv

ous

syst

em

depre

ssio

n

PH

YSIC

AL H

AZARD

S:

Fla

mm

able

liq

uid

and v

apor. V

apor

may c

ause

fla

sh f

ire

PO

TEN

TIA

L H

EALT

H E

FFECTS:

INH

ALA

TIO

N:

SH

ORT T

ERM

EXPO

SU

RE:

irrita

tion,

nause

a, vom

itin

g, difficu

lty b

reath

ing,

Good info

for

labelin

g c

onta

iners

What

happens

when e

xpose

d?

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

84

SKIN

CO

NTACT:

SH

ORT T

ERM

EXPO

SU

RE:

irrita

tion

LO

NG

TERM

EXPO

SU

RE:

sam

e a

s eff

ect

s re

port

ed in s

hort

term

exposu

re

EYE C

ON

TACT…

IN

GESTIO

N…

CARCIN

OG

EN

STATU

S:

OSH

A:

N

NTP:

N

IARC:

N

SECTIO

N 4

. FIR

ST A

ID M

EASU

RES

INH

ALA

TIO

N…

SKIN

CO

NTACT…

EYE C

ON

TACT…

IN

GESTIO

N…

SECTIO

N 5

. FIR

E F

IGH

TIN

G M

EASU

RES

What

should

you d

o if

expose

d?

Does

it c

ause

cance

r?

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

85

SECTIO

N 6

. ACCID

EN

TAL R

ELEASE M

EASU

RES

AIR

RELEASE:

Reduce

vapors

with w

ate

r sp

ray

SO

IL R

ELEASE:

Dig

hold

ing a

rea s

uch

as

lagoon, pond o

r pit f

or

conta

inm

ent.

Abso

rb w

ith…

SECTIO

N 7

. H

AN

DLIN

G A

ND

STO

RAG

E

Sto

re a

nd h

andle

in a

ccord

ance

…

SECTIO

N 8

. EXPO

SU

RE C

ON

TRO

LS, PERSO

NAL P

RO

TECTIO

N

EXPO

SU

RE L

IMIT

S:

METH

YL E

TH

YL K

ETO

NE:

METH

YL E

TH

YL K

ETO

NE:

200 p

pm

(590 m

g/m

3)

OSH

A T

WA

300 p

pm

(885 m

g/m

3)

OSH

A S

TEL

200 p

pm

(590 m

g/m

3)

ACG

IH T

WA

300 p

pm

(885 m

g/m

3)

ACG

IH S

TEL

8 h

r avg

15 m

in a

vg

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

86

SECTIO

N 9

. PH

YSIC

AL A

ND

CH

EM

ICAL P

RO

PERTIE

S

CO

LO

R:

colo

rless

PH

YSIC

AL F

ORM

: liq

uid

O

DO

R:

min

ty, sw

eet

odor

MO

LECU

LAR W

EIG

HT:

72.1

2

MO

LECU

LAR F

ORM

ULA

: C-H

3-C

-H2-C

-O-C

-H3

BO

ILIN

G P

OIN

T: 1

76 F

(80 C

) FREEZIN

G P

OIN

T: -

123 F

(-8

6 C

) VAPO

R P

RESSU

RE:

100 m

mH

g @

25 C

VAPO

R D

EN

SIT

Y (

air =

1):

2.5

SPECIF

IC G

RAVIT

Y (

wate

r =

1):

0.8

054

WATER S

OLU

BIL

ITY:

27.

5%

PH

: N

o d

ata

ava

ilable

VO

LATIL

ITY:

No d

ata

ava

ilable

O

DO

R T

HRESH

OLD

: 0.2

5-1

0 p

pm

EVAPO

RATIO

N R

ATE:

2.7

(eth

er

= 1

) VIS

CO

SIT

Y: 0

.40 c

P @

25 C

SO

LVEN

T S

OLU

BIL

ITY:

alc

ohol, e

ther, b

enze

ne, ace

tone,

oils

, so

lvents

MEK v

apor

is h

eavie

r th

an a

ir

MEK liq

uid

will

flo

at

on s

tagnant

wate

r

Will

lik

ely

sm

ell

MEK b

efo

re b

ein

g

overe

xpose

d

MYTH

: if it

smells

bad it

is h

arm

ful, if

it

smells

good it

is s

afe

Not

very

solu

ble

in w

ate

r

Goes

to v

apor

easy

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

87

SECTIO

N 1

0. STABIL

ITY A

ND

REACTIV

ITY

SECTIO

N 1

1. TO

XIC

OLO

GIC

AL

INFO

RM

ATIO

N

SECTIO

N 1

2. ECO

LO

GIC

AL IN

FO

RM

ATIO

N

SECTIO

N 1

3. D

ISPO

SAL C

ON

SID

ERATIO

NS

SECTIO

N 1

4. TRAN

SPO

RT I

NFO

RM

ATIO

N

SECTIO

N 1

5. REG

ULA

TO

RY IN

FO

RM

ATIO

N

SECTIO

N 1

6. O

TH

ER I

NFO

RM

ATIO

N

MSD

S’s h

ave a

n

abundance

of

info

rmation u

sefu

l in

many d

iffe

rent

asp

ect

s

Und

erst

andi

ng M

SD

S’s

, Jul

y 20

12

88

ww

w.n

asa.

gov

89

Awards

NASA Student Launch AwardsAward: Award Description: Determined by: When awarded:

Vehicle Design Award

Awarded to the team with the most creative and innovative overall vehicle design for their intended payload while still maximizing safety and efficiency.

Review Panel Launch Day

Payload Design Award

Awarded to the team with the most creative and innovative payload design while maximizing safety and science value. Review Panel Launch Day

Safety Award Awarded to the team that demonstrates the highest level of safety according to the scoring rubric.. Review Panel Launch Day

Project Review (CDR/FRR) Award

Awarded to the team that is viewed to have the best combination of written reviews and formal presentations Review Panel Launch Day

Educational Engagement Award

Awarded to the team that is determined to have best inspired the study of rocketry and other science, technology, engineering, and math (STEM) related topics in their community. This team not only presented a high number of activities to a large number of people, but also delivered quality activities to a wide range of audiences.

Review Panel Launch Day

Web Design Award Awarded to the team that has the best, most efficient Web site with alldocumentation posted on time. Review Panel Launch Day

Altitude Award Awarded to the team that achieves the best altitude score according to the scoring rubric and listed requirements. Review Panel Launch Day

Best Looking Rocket

Awarded to the team that is judged by their peers to have the “Best Looking Rocket” Peer Review Launch Day

Best Team Spirit Award

Awarded to the team that is judged by their peers to display the “Best Team Spirit” on launch day. Peer Review Launch Day

Rookie AwardAwarded to the top overall rookie team using the same criteria as the Overall Winner Award. (Only given if the overall winner is not a rookie team).

Review Panel June 13, 2014

Overall Winner Awarded to the top overall team. Design reviews, outreach, Web site, safety, and a successful flight will all factor into the Overall Winner. Review Panel June 13, 2014

92

National Aeronautics and Space Administration

George C. Marshall Space Flight CenterHuntsville, AL 35812www.nasa.gov/marshall

www.nasa.gov

NP-2013-11-129-MSFCG-35553