A comparative-advantages study is made of two different Martian atmospheric entry maneuvers, on the basis of calculation results for the case of a vehicle with a maximum L/D ratio of 2.3. Entries from a highly elliptical Martian orbit at 5 km/sec are more difficult than those from a lower altitude and speed orbit at 3.5 km/sec, due to their more stringent guidance requirements. Efforts to reduce the deceleration for the higher speed entry by lift-modulation achieved a 40-percent reduction, but at the cost of a 50-percent decrease in lateral range. The lower-speed entry's gliding trajectory is noted to encounter a far more benign atmospheric environment.
Atmospheric maneuvering during Martian entry
AIAA Atmospheric Flight Mechanics Conference ; 1988 ; Minneapolis, MN, United States
1988-01-01
Conference paper
No indication
English
Atmospheric maneuvering during Martian entry
AIAA | 1988
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