Computer Science
Scientific paper
Mar 1976
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1976kosis..14..302b&link_type=abstract
Kosmicheskie Issledovaniia, vol. 14, Mar.-Apr. 1976, p. 302-305. In Russian.
Computer Science
Lift Drag Ratio, Mars Landing, Soft Landing, Spacecraft Design, Ballistics, Design Analysis, Spacecraft Configurations, Spacecraft Reentry
Scientific paper
The minimum design lift/drag ratio of a wingless guided vehicle capable of landing on the Martian surface is selected as basic control variable. The minimum velocity at the instant the soft landing system is activated and the load on the frontal surface are also rated high in importance, while thermal, dynamical, and component or subsystem problems are viewed as secondary. The effect of various parameters on re-entry corridor width is examined, and the behavior of various Mars vehicle configurations (segmented, tapered frontal shields, 'boat' shapes, flat plate forms) is compared, for different assigned weights and sizes. It is concluded that the lift-drag ratio of a Mars landing module with roll control should be based on assurance of a safe landing within the re-entry navigation corridor.
Boiko A. S.
Ivanov Nikolai M.
Kariagin V. P.
Kremnev Roald S.
Martynov Iu. A.
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