For unmanned Mars exploration it is shown that structural and decelerator considerations can have significant influence on system configuration and selection; since capsule aeroshell provides major portion of velocity reduction, influence of structural design options on evolution of aeroshell configurations is examined; relative efficiencies of various decelerators are also studied, and potential of advanced configuration to enhance mission capability is indicated; system requirements of landing phase in which retro-engines and/or impact attenuation system are employed. (28752)
Structural and decelerator design options for Mars entry
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 6 , n 1
1969
6 pages
Article (Journal)
English
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Uncertainty Analysis of Mars Entry Flows over a Hypersonic Inflatable Aerodynamic Decelerator
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