2001 Mars Odyssey Aerobraking

摘要

The Mars Odyssey spacecraft was inserted into a highly elliptical capture orbit about Mars on 24 October 2001. To establish the required science mapping orbit, the propulsive capabilities of the spacecraft were supplemented by aerobraking. The necessary orbital period reduction was achieved by 332 successive aerobraking drag passes over a 76-day time period. The strategy, implementation, and results of the aerobraking phase of the mission are detailed. Aerobraking subphases, constraints, modeling, maneuver logic, trajectory characteristics, and key decisions are described. Differences between Odyssey and the Mars Global Surveyor aerobraking experiences are included.