Optimization of aerobrake assisted descent trajectories at Mars

Details Optimization of aerobrake assisted descent trajectories at Mars Optimization of aerobrake assisted descent trajectories at Mars

Jan 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991aiaa.meetqy...c&link_type=abstract

AIAA, Aerospace Sciences Meeting, 29th, Reno, NV, Jan. 7-10, 1991. 11 p.

Physics

Aerobraking, Descent Trajectories, Earth-Mars Trajectories, Interplanetary Transfer Orbits, Lift Drag Ratio, Optimization, Aerodynamic Heating, Mars Atmosphere, Mars Surface, Return To Earth Space Flight

Scientific paper

This paper examines considerations pertinent to the use and design of Martian aerobraking descent vehicles having lifting characteristics. It focuses on optimizing descent trajectories to maximize the cross range of an aerobrake vehicle which has a maximum lift-to-drag ratio of 1.2 and ballistic coefficient of 28 lb/sq ft. Cross range translates into the capability of the vehicle to reach desired landing sites from a variety of minimum energy interplanetary transfers and the resulting Mars' parking orbits. This type of aerobrake was found to yield substantial cross range of over 1000 nmi. A Mars descent aerodynamic heating analysis is also presented for the 'worst case' trajectory studied, showing the maximum descent heating rate to be 8.0 BTU/sq ft per sec with a maximum temperature of 1650 F.

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