Summary of parametric investigation of parachute recovery system for Mars entry vehicle is presented; parameters investigated were entry vehicle velocity, entry angle, estimated atmospheric variations as of mid 1962 and parachute system weight; analysis shows that under most severe expected entry conditions four minute time of descent cannot be achieved using conventional parachute designs; three-stage system with first stage deployed at maximum dynamic pressure of 500 psf, weighing 17 lb, would provide minimum weight decelerator system.
Recovery system for controlled descent through Martian atmosphere
Symposium Ballistic Missile Space Technology -- Trans
8th Symposium on Ballistic Missile and Space Technology ; 1963 Recovery
1963
29 pages
Conference paper
English
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Influence of seasonal cycles in Martian atmosphere on entry, descent and landing sequence
Online Contents | 2014
|NTIS | 1992
|Terminal descent controlled vehicle recovery
AIAA | 1984
|