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NASA USLI – PDR

NASA USLI – PDR VU Aerospace Club Rocket-based Studies of Thermoelectric Exhaust Heat Recovery in Aerospace Engines. Project Overview . Recover waste heat from exhaust Use thermo electric generators (TEG) Initial Testing for: Recovered Heat Thrust Losses

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NASA USLI – PDR

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  1. NASA USLI – PDR VU Aerospace ClubRocket-based Studies of Thermoelectric Exhaust Heat Recovery in Aerospace Engines

  2. Project Overview • Recover waste heat from exhaust • Use thermo electric generators (TEG) • Initial Testing for: • Recovered Heat • Thrust Losses • Use rocket to simulate flight conditions of jet

  3. Application • Use thermoelectric generators to recover waste heat coming off of jet engines • Commercial jets run for hours at a time • Can recover energy to power on-board systems during flight • Small improvements = big benefits on large scale

  4. Motivation • Energy efficiency is important global topic • Typical jet engines run at 35% efficiency • Small increases in efficiency can pay large dividends • Test for net increase in efficiency • Rocket is cheapest means of testing theory while achieving in-flight operating conditions

  5. Payload Description • Thermoelectric Generators (TEGs) will recover waste heat in exhaust flow • Attach TEG assembly on aft end of rocket • Voltages read and stored on-board by data logger

  6. Thermoelectric Generator • Allows for direct conversion between thermal and electrical energy • Function through motion of excess electrons and the Seebeck Effect • Very reliable since no moving parts • Lightweight

  7. Payload Verification/Testing • Testing facility to measure power output as function of: • Geometry • Temperature difference • Flow rate • LabVIEW used to measure and record: • Temperatures • Voltages • Initial tests determine optimal electrical resistance

  8. Data Acquisition • Using SparkFunLogomatic V2 microSDDataloggers on board. • Each board has up to 10 channels. • Low cost and recording to SD makes accessing data simple.

  9. Data Acquisition Layout SD Cardash MCU Vout A/D Resistor bank TEG + - + - TEG

  10. Rocket Dimensions & Weight • Length: 125 in • Diameter: 6.3 in • Span Dia.: 26.3 in • CG: 89.9 in • Stability Margin: 1.86 • Launch Mass: 16.8 kg • Thrust-to-Weight: 3.69 • CP: 101.3 in Electronics Bay

  11. Rocket Materials • Dyna-wind body tube • Carbon Fiber Composite Fins for added stability • AV Bay located in coupler tubing • Break-away wiring will allow for data collection until recovery deployment

  12. Verification and Testing • Motor • Static testing • Thrust effects of payload • TEG location • Number of TEGs • Preliminary Flights • Safe take-off velocity • Full-scale flight

  13. Integration • Utilizing microSD to log data on-board • System small enough to make redundant collection viable • Breakaway connectors eliminate wiring concerns • Mounting options: • Fixed to airframe • Threaded on motor retainer

  14. Motor • Cesaroni Pro98 L610 • Long burn (8.1s) • Aeropack Retainer • Thrust to weight: • 5.4 (initial) • 3.7 (average)

  15. Recovery System • Dual deploy recovery system • Static firing to test deployment • 12-14’ main chute with 24-36” drogue chute • Fireball used to prevent zippering • Black powder charges • Redundant systems using PerfectfliteminiAlt/WD

  16. Rocket Safety • Static fires to characterize thrust • All components used to industry standards • Stability margin within safe range • Scaled and preliminary flights • All codes and laws followed during all team events

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