Propagating Interplanetary Trajectories from Earth to Mars
Numerically integrate the orbital equations of motion of an Earth to Mars interplanetary trajectory.
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PDF document and a MATLAB script called pprop_e2m that can be used to numerically integrate the geocentric and heliocentric orbital equations of motion of an Earth to Mars interplanetary trajectory. This scientific simulation begins at a user-defined epoch and state vector somewhere within the Earth’s sphere-of-influence (SOI) and ends at (1) closest approach to Mars, (2) a user-defined Mars-centered (areocentric) distance, or (3) at a user-defined final epoch.
Cite As
David Eagle (2026). Propagating Interplanetary Trajectories from Earth to Mars (https://www.mathworks.com/matlabcentral/fileexchange/41356-propagating-interplanetary-trajectories-from-earth-to-mars), MATLAB Central File Exchange. Retrieved .
General Information
- Version 1.2.0.0 (15.9 MB)
MATLAB Release Compatibility
- Compatible with any release
Platform Compatibility
- Windows
- macOS
- Linux
| Version | Published | Release Notes | Action |
|---|---|---|---|
| 1.2.0.0 | Trajectory now initialized and results displayed in the Earth mean equator and equinox of J2000 (EME2000) coordinate system. Code clean up. |
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| 1.1.0.0 | Updated ephemeris to use DE421.bsp data file. Geocentric and heliocentric orbits displayed in Earth true-of-date coordinate system. Updated PDF documentation. |
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| 1.0.0.0 |
