Parametric study was conducted to determine performance of soft lander using two distinct thrust levels during terminal phase of out-of-orbit entry; analysis is applicable to vehicle descending along trajectory governed by gravity turn maneuver; with residual landed fraction as performance criterion, superiority of dual thrust-level concept as compared to single thrust-level model was demonstrated and tabulated; entry conditions, atmospheric profile, ballistic coefficient, thrust levels, and entry mass were variables used in determining optimum ignition altitudes for single and dual thrust-level systems.
Performance of mars soft lander with staged propulsion
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 7
1968
7 pages
Article (Journal)
English
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Performance of a Mars soft lander with staged propulsion
AIAA | 1967
|SAE Technical Papers | 1968
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