CubeSat-Class Spinning Landers for Mars Rex Ridenoure Ecliptic Enterprises Corporation Mars CubeSat/NanoSat Workshop JPL 2014 Nov 20-21.

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Presentation transcript:

CubeSat-Class Spinning Landers for Mars Rex Ridenoure Ecliptic Enterprises Corporation Mars CubeSat/NanoSat Workshop JPL 2014 Nov 20-21

1961

1985

From Dual-Spin Spinning Spacecraft to Spinning Lander Despun Section Spun Section Spinning Lander* + = Leg System Landing Radar + * U.S. patent # ; foreign patents pending

Size Comparison for GLXP Win

Why Consider Spinning vs. 3-Axis Landers? Proven dual-spin system robustness and scalability Avionics and flight software ~1/3 as complex Propulsion ~1/2 as complex Single landing radar vs. 3 No chance of tip-over at landing Excellent hopping capability (mobility) Overall development and I&T ~1/2 as complex Potential for significantly lower total mission cost

CubeSat-Class Spinning Lander ~12-15 kg total mass; ~6 min. hovering capability; ~2-4 km hopping capability

Possible Mars Applications for CubeSat-Class Landers For expanded mobility around larger landers For rugged terrain not suitable for rovers Distributed science from a common EDL system Targeted landers from Mars balloons or airships As a MAV-like element in sample return architectures? Phobos/Deimos landers?

Rex Ridenoure (626)