A six-degree-of-freedom guidance and control analysis of Mars aerocapture

Details A six-degree-of-freedom guidance and control analysis of Mars aerocapture A six-degree-of-freedom guidance and control analysis of Mars aerocapture

Jan 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992aiaa.meetqt...p&link_type=abstract

AIAA, Aerospace Sciences Meeting and Exhibit, 30th, Reno, NV, Jan. 6-9, 1992. 11 p.

Mathematics

Logic

Aerobraking, Aerocapture, Manned Mars Missions, Spacecraft Control, Spacecraft Guidance, Degrees Of Freedom, Flight Control, Predictor-Corrector Methods, Reentry Trajectories, Spacecraft Reentry

Scientific paper

A six-degree-of-freedom (6DOF) simulation is developed to investigate the control and guidance issues of a Mars aerobraking vehicle. The guidance algorithm used is a predictor-corrector guidance formulation designed to control the exit orbital apoapsis and wedge angle using bank-angle modulation. Major features of this predictor-corrector guidance algorithm include: (1) integration of the 3DOF equations of motion within an inner-loop simulation; (2) load-relief logic; (3) finite roll rates; and (4) an aerodynamic feedback multiplier. The algorithm is capable of successfully guiding the vehicle through combinations of atmospheric density dispersions, aerodynamic mispredictions, and off-nominal atmospheric interface conditions. This study demonstrated that the addition of vehicle dynamics to the Mars aerobraking simulation does not significantly impact mission feasibility. That is, a robust control system design coupled with an adaptive guidance algorithm can assure mission success in the presence of numerous off-nominal conditions.

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