Mars Airplane Thermoelectric Carbon Dioxide Propellant Generator Paul Rosensteel Michael McVey...

Mars Airplane Thermoelectric Carbon Dioxide Propellant Generator

Paul Rosensteel

Michael McVey

Advisor: Dr. Robert Ash

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

Mars AirplaneMars Airplane

Propulsion Unit

Problem StatementProblem 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

Mars ConditionsMars 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.

Thermoelectric DeviceThermoelectric Device

Peltier EffectPeltier Effect

Ultrasonic Distance DetectorUltrasonic Distance Detector

Ultrasonic Ultrasonic DeviceDeviceSchematicSchematic

Ultrasonic Sensor CircuitUltrasonic Sensor Circuit

Sensor SetupSensor Setup

Vacuum Chamber SetupVacuum Chamber Setup

Vacuum Chamber SetupVacuum Chamber Setup

MeasurementsMeasurements

Chamber PressureChamber TemperatureTH and TC of TE Device

TR Heat Sink Temperature

Dry Ice Layer Thickness – Range DetectorDevice Power

Experimental DataExperimental Data

Experimental Run Two

-90-80-70-60-50-40-30-20-10

030 60 90 12

015

018

021

024

030

033

036

0

Time (s)

Tem

per

atu

re (

deg

C)

Chamber Temperature

Resevoir Temperature

Hot Side Temperature

Cold Side Temperature

Experimental DataExperimental 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

ConclusionsConclusions

Improved experimental design setup.

More robust equipment required.Dry ice production possible.Feasible propellant option.

Safety and EnvironmentalSafety 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.

ImprovementsImprovements

Higher capacity Peltier device.Chamber dimension:

1) Pressure Chamber

2) Smaller volume – 1100cm3 vs. 0.1m3

3) Thermal Isolation of connectionsCooling method – Liquid Nitrogen

COCO22 Propulsion Propulsion

Questions and Answers