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

2. 1961

3. 1985

4. 2007-2008

5. From Dual-Spin Spinning Spacecraft to Spinning Lander Despun Section Spun Section Spinning Lander* + = Leg System Landing Radar + * U.S. patent #20090206204; foreign patents pending

6. Size Comparison for GLXP Win

7. 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

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

9. 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?

10. Rex Ridenoure rridenoure@eclipticenterprises.com (626) 278-0435