Rapid Advanced Heliocentric Mission Design for L3, L4, L5, NEO Rendezvous, Capture, Sample Return, Year 3
Status: Completed
Start Date: 2014-11-01
End Date: 2015-10-01
Description:
Provide fast, new capability for low energy orbit missions with SEP & sail propulsion.
Benefits:
Enable New Class of Missions, Especially SmallSats. Low Energy Heliocentric Orbits, Lunar Orbits, Sun-Earth-Moon 4 Body Orbits. Sail & Impulsive Trajectory in Restricted 3 & 4 Body Problems. Missions: Lunar Orbits, Earth-Moon Flybys, Heliophysics Constellations, Solar Polar, NEO Capture/Deflection, L3, L4, L5, Lunar Libration. Enable Low Cost Interplanetary SmallSat Missions. Solar Sail Often Critical For SmallSats, e.g. Lunar Flashlight, Scoutsat, Heliophysics L5 Constellation. Reduce Labor, Time, & Cost for Advanced Design, Studies, Proposals.
Lead Organization: Jet Propulsion Laboratory