Trajectory Design for the Phobos and Deimos & Mars Environment Spacecraft
Trajectory Design for the Phobos and Deimos & Mars Environment Spacecraft
- New search for: A. L. Genova
- New search for: D. J. Korsmeyer
- New search for: M. E. Loucks
- New search for: F. Y. Yang
- New search for: P. Lee
- New search for: A. L. Genova
- New search for: D. J. Korsmeyer
- New search for: M. E. Loucks
- New search for: F. Y. Yang
- New search for: P. Lee
The presented trajectory design and analysis was performed for the Phobos and Deimos & Mars Environment (PADME) mission concept as part of a NASA proposal submission managed by NASA Ames Research Center in the 2014-2015 timeframe. The PADME spacecraft would be a derivative of the successfully flown Lunar Atmosphere & Dust Environment Explorer (LADEE) spacecraft. While LADEE was designed to enter low-lunar orbit, the PADME spacecraft would instead enter an elliptical Mars orbit of 2-week period. This Mars orbit would pass by Phobos near periapsis on successive orbits and then raise periapsis to yield close approaches of Deimos every orbit thereafter.
Document information
Trajectory Design for the Phobos and Deimos & Mars Environment Spacecraft
2016
12 pages
Report
No indication
English
Astronomy & Astrophysics , Extraterrestrial Exploration , Astronautics , Spacecraft Trajectories & Flight Mechanics , Deimos , Elliptical orbits , Flyby missions , Mars (planet) , Orbital velocity , Orbit calculation , Phobos , Spacecraft trajectories , Trajectory analysis , Mars environment , Gravitational fields , Lunar orbits , Neutron spectrometers , Runge-kutta method , Escape velocity
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