Mars entry-to-landing trajectory optimization and closed loop guidance

Details Mars entry-to-landing trajectory optimization and closed loop guidance Mars entry-to-landing trajectory optimization and closed loop guidance

Aug 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991ads..confq....i&link_type=abstract

AAS and AIAA, Astrodynamics Specialist Conference, Durango, CO, Aug. 19-22, 1991. 48 p.

Astronomy and Astrophysics

Astronomy

Atmospheric Entry, Descent Trajectories, Mars Atmosphere, Trajectory Optimization, Trajectory Planning, Aerobraking, Aeromaneuvering, Flight Control, Mars Sample Return Missions, Mars Surface Samples, Terminal Guidance

Scientific paper

The guidance strategy of the Mars Rover Sample Return mission is presented in detail. Aeromaneuver versus aerobrake trades are examined, and an aerobrake analysis is presented which takes into account targeting, guidance, flight control, trajectory profile, delivery accuracy. An aeromaneuver analysis is given which includes the entry corridor, maneuver footprint, guidance, preentry phase, constant drag phase, equilibrium guide phase, variable drag phase, influence of trajectory profile on the entry flight loads, parachute deployment conditions and strategies, and landing accuracy. The Mars terminal descent phase is analyzed.

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