A MODEL COMPARISON FOR OPTIMAL MARS ASCENT TRAJECTORIES

Abstract

Maximum payload Mars launch trajectories are computed for a nominal two-stage Mars ascent vehicle. This vehicle transfers a payload from the surface of Mars to a circular parking orbit about Mars in preparation for transferring the payload to an Earth return vehicle. Both gravity turn and pitch-rate control models for controlling the ascent vehicle's trajectory are investigated. For each case, a rather complicated nonlinear programming problem is obtained and then solved using a sequential quadratic programming algorithm.

KEY WORDS:

• Trajectory optimization
• optimal control
• launch vehicle design
• gravity turn trajectories
• Mars rover/sample return mission.

Additional information

Notes on contributors

JOSEPH E. FANNING

Currently, Booster Operations Controller, United States Air Force, Vandenberg Air Force Base, California 93437, U.S.A.