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Aerospace Engineering Sciences

Capstone

Senior Design ProjectsASEN 4018/4028

How they prepare students for the workforce

Jean N. KosterUniversity of Colorado

December 15, 2008

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REAL WORLD STATUS 2008

20% Of the Workforce Is Eligible To RetireToday

One-third Of the Workforce Eligible ToRetire In 5 Years

One-half Of the Workforce Eligible ToRetire In 10 Years

Greg Enders, LMCO 2

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AES Senior Projects StructureCourse

Coordinator

2 PAB Advisors

2 PAB

Advisors

2 PAB Advisors

2 PAB Advisors

ElectronicsTrudy Schwartz

MachinistMatt Rhode

2 PAB Advisors

2 PAB

Advisors

2 PAB Advisors

2 PAB Advisors

TEAM 1

Customer1

7-10Students

TEAM 2

Customer2

7-10Students

TEAM 3

Customer3

7-10Students

TEAM 4

Customer4

7-10Students

TEAM 5

Customer5

7-10Students

TEAM 6

Customer6

7-10Students

TEAM 7

Customer7

7-10Students

TEAM 8

Customer8

7-10Students

Project Advisor Board (PAB) Total 9 faculty (1 course credit) and 2 staff 1 Course Coordinator (Jean Koster, 2008)8 Faculty Team Advisors; advising 2 different teams eachEach advisor team is differentStaff advisors: Matt Rhode and Trudy Schwartz

Maximum 8 Teams

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Senior Projects Team Structure

ProjectManager

Subsystem 1Lead Engineer

CFO SafetyEngineer

Customer 2 PAB Advisors

ManufacturingEngineer

SystemsEngineer

Subsystem 2Lead Engineer Subsystem 3Lead Engineer Subsystem 4Lead Engineer

Common Subsystems:Mechanical Electrical Software Aerodynamics Structures Thermal

5

Teams operate like small entrepreneurial businesses

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Course Milestones

Progress Evaluation Process:1. Starting Point: Customer Project Proposal (Requirements)2. Project Definition Document (PDD)3. Conceptual Design Document (CDD)4. Preliminary Design Review (PDR)

5. Critical Design Review (CDR)6. Fall Final Report7. Spring Manufacturing Interim Reviews (IR1, IR2)8. AIAA Student Regional Conference Paper

9. Final Project Review (FPR)10. Spring Final Report (SFR)11. ITLL Public Expo

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Deliverables 1 (PDD)

Customer Requirements Project Definition (PDD) Background, Goal, Objectives, Functional Block Diagram,Concept of Operations

Top level Project Requirements (0.PRJ.x)

Top level System Requirements (0.SYS.x) Minimum Requirements for Success Deliverables Technical and Financial Risks Team formation and Team Expertise Resources

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Deliverables 2 (CDD)

Project Definition Conceptual Design (CDD) Team information System Architecture (3 design options)

Requirements (3-5 most important reqs., rank) Feasibility (for top ranked architecture option) Testing and Verification requirements for key systems Assess key risks and mitigation options

Assess team qualifications Respond to criticism received on PDD Resources update

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ASEN 401810

Choosing System Architecture

Wheeled Spider

UAV

Snake Roller

Tracked

System concept baseline study selected wheeled architecture

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Deliverables 3 (PDR)

Conceptual Design Preliminary Design (PDR) Development and assessment of system design options;arguments for chosen architecture

Flow-down from functional needs to identified requirements

System Design-To specifications. Development andassessment of subsystem design options and design-tospecifications

Preliminary itemization of required performance parameters

Project Feasibility Analysis and Risk Analysis Define high risk sub-system for prototyping Back-of-the-envelope, Matlab, preliminary analysis or test Define optional off -ramps

Project Management Plan (preliminary) Myers-Briggs analysis 11

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Oral Presentations PDR, CDR

Presentation to 11 PAB members and entire body of students Presentations: 50 minutes: 25 min presentation and 25 min Q&A Every student must present at least once at PDR and CDR

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System Breakdown StructureProject: MARVLIS - 2007

6 Dimension, 10 min Endurance, Image Capture/Transmission with location,Launch Capability

Propulsion

Legend

Sub-Subsystems

Subsystems

SystemRequirements

Aerodynamics Electronics LauncherStructures

Propeller

Motor/Gearbox

BatteriesTail/Stabilizers

ControlSurfaces

Camera

Receiver

GPS

SpeedController

Servos

Spring

TelescopingLeg

Airframe

Planform

Aerodynamics

Airfoil

Materials

LaunchElectronics

MAV Interface

December 16, 2008 MARVLIS 13

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Design-To Specifications

Preliminary Design Review 14

Mother Rover Design-To Specifications1. Baseline weight of 100 lbf.

2. Baseline dimensions of 3.5 ft. wide x 3.5 ft. long x 2.0 ft. high3. Base of Mother = 4.25 in. from ground level

4. Mounted camera must see Children at all times

(representative model only)

Ramp Design-To Specifications1.Length of ramp is greater than length of

Child rover2.Ramp is 3x wider than Child rover

3.Ramp is placed on front or back of Motherrover only

4.Ramp will have -in. ground clearance

Child Rover Design-To Specifications1. Baseline weight of 15 lbf.

2. Baseline dimensions of 10 in. wide x 10 in. long x 8 in. high

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Aerodynamics Risk

Justifications: Wings too small

Cannot take off in 75 ft, use batteriestoo fast

Mitigation: Prototyping Improperly sized tail

Plane is unstable & uncontrollable Mitigation: Margin & prototyping

Improperly sized control surfaces Aircraft is uncontrollable Mitigation: Extra analysis & margin

Insufficient directional stability

Aircraft stability is unknown and notconsidered

Mitigation: Adding a vertical fin &deflecting single rudder in turn, use dragto turn

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Improperlysized tail

Insufficientdirectional

stability

Wings toosmall

Improperlysized control

surfaces

Possibility

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Deliverable 4 (CDR)

System Architecture is fully documented at CDR All subsystems are checked for feasibility and are given a go Sub-system decomposition and integration is understood

Mechanical, electrical, and software elements are analyzed All blue-prints are ready to enter the fabrication process

Interfaces between sub-systems are working well Integration of sub-systems into units is understood

Manufacturing and System Integration Plan The Testing and Verification Plan is finalized

Test concepts of operation are documented Project Management Plan (PMP) is finalized The System Engineer signed off on the proposed design Manufacturing of components starts after successful completion of

CDR.

B. S. Blanchard, W.J. Fabrycky, Systems Engineering and Analysis, Prentice Hall,2006.16

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System Design

Critical Design Review

1. Primary Vehicle (PV) On-board PIC controls the DeploymentMechanism (DM) through Command andData Handling (CDH) Pilot controls the control surfaces

2. Deployment Mechanism (DM)

Consists of mounting point for the SV andlinear actuator for pin-movement Attached to the PV with bracketing system

3. Sub-Vehicle (SV) CUPIC autopilot controls the controlsurfaces and motor settings through CDH Payload is supplied with its own power

SystemArchitecture

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Design

Critical Design Review

Deployment Mechanism Design Actuator pulls a pin

Pin removes attachment to SV

DM weighs 9g

DM mounted to an aluminum beam

DeploymentMechanismMDE

The SVs shall be deployed on demand. The DM shall weigh no more than 13 g The DM shall be mounted on a rod (the bracket) capable of

withstanding the expected loads.

Deployment Mechanism Design-To Specs

Prototype & Testing Results Under vibrations from 0 Hz to 150 Hz, successful

deployment 121/124 trials

Confidence of 95 % in vibrations During simulated aerodynamic loading, successfuldeployment 20/20 trials

Confidence of 99 % in aerodynamic loading

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ASEN 4018 19

Matlab Model

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ASEN 4018 20

Need thicker boom due to deflection at max load.

Based on experimental data: OD = .312 for 1.5 deflection (+1.3oz)

0 5 10 15 20 25

-10

-9

-8

-7

-6

-5

-4

-3

-2

-1

0 Tail Boom Test Load versus Displacement

Load (lbs)

D i s p

l a c e m e n

t ( i n

)

Experimental

Theoretical

3.65" At EstimatedMax Load

Failure at23lbs8.75"

Experimental Verification & Prototyping

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Educational Support

Lectures: Project Selection Conceptual design Defining Requirements Systems Engineering Mission Failures Project Management

Running Meetings Patent Law, IP Ethical Decision-Making Entrepreneurship

Workshops: System Engineers Program Managers Team working Fabrication (9) Measurements Electronics

Power Systems Composite Fabrication Safety Fire

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http://www.colorado.edu/ASEN/SrProjects

Example of ITLL Poster Presentation

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http://www.colorado.edu/ASEN/SrProjectshttp://www.colorado.edu/ASEN/SrProjects

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Senior Design Student Paper AwardsAIAA Reg. V Student Paper Conferences

2008 First Place, Team Division (KRAKEN senior project team) Second Place, Team Division (MARVLIS senior project team) Second Place, Graduate Division (Laurren Kanner)

2007 First Place , Graduate Division (Laurren Kanner) First Place , Team Division (SOARS senior project team) Best Student Paper , JANNAF Conference, Team MaCH-SR1

2002 First Place , Undergraduate Division (Otto Krauss MaCH-SR1)

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CU-AES Senior Design Webpage:http://www.colorado.edu/ASEN/SrProjects

AES Senior Design Network http://aesseniordesign.ning.com/

http://www.linkedin.com/groups?gid=159152

Contact:Jean.Koster@Colorado.edu

+(303)492-694524

http://www.colorado.edu/ASEN/SrProjectsmailto:Jean.Koster@Colorado.edumailto:Jean.Koster@Colorado.eduhttp://www.colorado.edu/ASEN/SrProjects

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History of Recent Projects - 1

BIRDIE Biologically-Inspired lowReynolds number DynamicImagery Experiment

To create an experimental apparatus that cantrace out a given wing motion similar to ahummingbird in hovering flight

DIABLO De-rotated Imager of theAurora Borealis in Low-Earth Orbit

Provide a spinning satellite with a de-rotatedimaging system

D-SUAVE Deployable Small UAVExplorer To design, fabricate, integrate and verify a RCcontrolled UAV capable of being remotelydeployed from the ARES aircraft and flying aspecific flight pattern

PRV Peregrine Return Vehicle To provide the Colorado Space GrantConsortium with a reusable vehicle that canreturn student built science payloads to aselected target

SOARS Self Organizing AerialReconnaissance System

Design, build and test an autonomous aerialsystem (UAS) capable of imaging multipletargets within a 1 km circle as quickly aspossible with 99% probability of object detection(according to Johnson criteria)

SWIFT Supersonic Wind andImaging Flow Tunnel

Supersonic wind tunnel (Mach number 1.5 2.5)and flow visualization system operable by

undergraduate students

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History of Recent Projects - 2

VITL Vehicle for Icy TerrainLocomotion

Design and build a prototype for locomotionsystem of a vehicle exploring a Europa-like surfacecapable of traversing 1 km of icy terrain in 7 dayswith characteristic obstacles

BREW Bolt-on RacecarEnhancing Wing

Conceive, design, fabricate, integrate, test, andverify a device that allows the measurement of thedownforce and drag of any rear wing for present

and future CU FSAE carsCALAMAR-E Cavity Actuated Low-speed ActivelyManeuverable AquaticRover Experiment

Conceptualize, design, fabricate, test, and verifysynthetic jet actuators for a highly maneuverable,low speed under water vehicle

Flap and AileronReplacement System

Produce a wing that demonstrates roll controlwithout mechanical linkages by integration of

smart materials as actuatorsMaCH-SR1 Multi-disciplinary Conceive, design, fabricate, integrate, and verify aself-sufficient hybrid rocket engine

MARS Meteorological AerialResearch Sonde

Conceive, design, fabricate, and test a deployabledual-mode sonde system that will provide multi-unit communications ability capable of sustainedflight times and controlled flight

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History of Recent Projects -3

HARRV High Altitude ResearchReturn Vehicle

Design, build, test a return vehicle for scientificpayloads released from high altitude balloonsto proximity of balloon launch site

SPEC Space Elevator Climber Design a model space elevator system to competein the Spaceward Foundation Elevator 2010competition.

Short TakeOff Wing Design, fabricate , and characterize a FanWing

deviceHAVUC Heavy-lift Aerial Vehicle for the Conceive, design, fabricate, integrate, test, andverify an un-inhabitated aerial vehicle (UAV) with aheavy-lift capability that has an empty weight nogreater than 10 lb; heavy-lift being defined as thepayload contributing a minimum of 60% to the totaltakeoff weight

SHARC Stable Handling Aerial Radio-controlled Cargo-testbed

Develop a low-cost, easy to operate, and reliableaerial vehicle for testing of sensor payloads

CUBDF Design-Build-Fly Design, build, fly a high-volume payloadcompetitive aircraft after AIAA competitionguidelines.

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History of Recent Projects -4

APTERAAero-Braking Project ToEffectively Reduce Altitude Design, build, and test a deployable devicewhich will increase aerodynamic drag with the

intent of changing the orbit of the DANDEsatellite from 600km to 350km within 300 days.

Mach-SR1 Multi-disciplinary Hybrid StudentRocket Project

design, build, test, integrate feed, injection andignition subsystems into a flight configuration for ahybrid rocket to deliver a 0.5 kg payload to analtitude of 4,500 m.

KRAKEN Kinematically RovingAutonomously controlled Electro-Nautic

Design, build, competitively test an unmannedunderwater vehicle equipped with vortex ringthrusters

MARVLIS Micro Air Reconnaissance VehicleLaunch and Imaging System

Design, fabricate, and test a micro air vehiclecapable of capturing an image and transmitting itwith a time and position stamp

ADAMSS Aerially Deployed AutonomouslyMonitored Surface Sensors

Design and build a system that can remotely placelow-cost disposable sensors, collect science data,and then retrieve this data all without on-site humaninteraction

ARCTIC Arctic Region Climate Trackingand Instrumentation Cargo

The goal is to develop a payload that provides arcticclimate data measurements at otherwiseinaccessible earth-fixed locations. The payload willbe constructed for an InSitu Insight A-20 UAV.

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