New concept results in family of compact shapes with lift-to-drag ratios of 0.5 to 1.0; main heat shield consists of circular cone raked off at angle to provide lifting surface; afterbody is elliptical cone fitted to forecone; trim at zero angle of attack results in symmetrical flow field over forebody which makes shape amenable to reliable analysis; re-entry criteria are evaluated in terms of aerodynamic and guidance requirements for speeds up to 65, 000 fps; operational trajectories are described; for re-entry at 65, 000 fps, heat-shield weight for six man vehicle is about one-third of total vehicle weight.
Configuration for re-entry from mars missions using aerobraking
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 2 , n 4
1965
7 pages
Article (Journal)
English
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