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Mars Airplane Thermoelectric Carbon Dioxide Propellant Generator Paul Rosensteel Michael McVey Advisor: Dr. Robert Ash

Mars Airplane Thermoelectric Carbon Dioxide Propellant Generator Paul Rosensteel Michael McVey Advisor: Dr. Robert Ash. NASA ARES (Aerial Regional-Scale Environmental Survey). Mars Airplane. Propulsion Unit. Problem Statement.

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Mars Airplane Thermoelectric Carbon Dioxide Propellant Generator Paul Rosensteel Michael McVey Advisor: Dr. Robert Ash

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  1. Mars Airplane Thermoelectric Carbon Dioxide Propellant Generator Paul Rosensteel Michael McVey Advisor: Dr. Robert Ash

  2. NASA ARES (Aerial Regional-Scale Environmental Survey)

  3. Mars Airplane Propulsion Unit

  4. Problem Statement • Develop a test bed for thermoelectric device application and viability as a renewable source of solid CO2 production for use as a propellant on the NASA ARES (Aerial Regional-Scale Environmental Survey ) Vehicle

  5. Mars Conditions • Atmosphere: 95.32% carbon dioxide, 2.7% nitrogen, 1.6% argon, 0.13% oxygen and 0.07% carbon monoxide with variable water content. • Pressure: 4.56 torr (0.006 atm). • Gravity: 37.95% (3.711m/s2) of Earth’s. • Temperature: Average surface temperature is 210 K and ranges from 185 to 235 K at the middle latitudes.

  6. Thermoelectric Device

  7. Peltier Effect

  8. Ultrasonic Distance Detector

  9. Ultrasonic DeviceSchematic

  10. Ultrasonic Sensor Circuit

  11. Sensor Setup

  12. Vacuum Chamber Setup

  13. Vacuum Chamber Setup

  14. Measurements • Chamber Pressure • Chamber Temperature • TH and TC of TE Device • TR Heat Sink Temperature • Dry Ice Layer Thickness – Range Detector • Device Power

  15. Experimental Data

  16. Experimental Data • Constant power of 10Watts applied. • Constant chamber pressure of 5.8 Torr. • No detected dry ice layer. • Gas composition 98% CO2, 2% misc. • QC = hASΔT = 0.069W • COP = 0.0069

  17. Conclusions • Improved experimental design setup. • More robust equipment required. • Dry ice production possible. • Feasible propellant option.

  18. Safety and Environmental • Carbon Dioxide build up during testing. • Handling of pressurized gas. • Electrical shock hazard potential. • Extreme cold exposure. • No hazardous gases or chemicals. • Recycling of Carbon Dioxide. • Solar power energy use.

  19. Improvements • Higher capacity Peltier device. • Chamber dimension: 1) Pressure Chamber 2) Smaller volume – 1100cm3 vs. 0.1m3 3) Thermal Isolation of connections • Cooling method – Liquid Nitrogen

  20. CO2 Propulsion Questions and Answers

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