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Spinning Descent and Compressed Gas Hopper Christine Troy Assistant Project Manager Webmaster Lunar Descent Attitude Control Analysis Design Alternative Evaluation 1 AAE450 Spring 2009 Christine Troy Attitude Problem Decrease mass, power, volume, cost, and/or integration complexity through design alternatives 1) Spinning lander on descent for attitude control 2) Compress gas with force of landing and release stored energy for hopping 2 AAE450 Spring 2009 Christine Troy Attitude Spinning Lander – Initial analysis: 1.7 kg attitude propellant savings • Increased complexity, small mass margin for required structural changes, not recommended for large payloads – New mass properties: 2.2 kg attitude propellant savings • Possible benefits for very small payloads Compressed Gas Hopper – Some or all travel could be obtained from bouncing using stored descent energy – Compressed gas not recommended – highly temperature sensitive, limited velocity and acceleration inputs • Commercial gas springs limited to approx. -23° to 82°C – Lunar surface temperature -153° to 107° C 3 AAE450 Spring 2009 Christine Troy Attitude References Rauschenbakh, Boris, Michael Ovchinnikov, and Susan McKenna-Lawlor. Essential Spaceflight Dynamics and Magnetospherics. Dordrecht, The Netherlands: Kluwer Academic Publishers, 2003. Wiesel, William. Spaceflight Dynamics. New York: McGraw-Hill, 1997. Howell, Kathleen. Notes from A&AE 440. Spring 2008. Dengel, Yunus and Michael Boles. Thermodynamics. Boston: McGraw-Hill, 2002. Industrial Gas Springs and Dampers. Enidine Product Guide. 2007. 4 AAE450 Spring 2009 Christine Troy Attitude