Problems that occur during manned earth entry in return from planetary missions are reviewed to evaluate current technology and systems concepts; analytical results show that lift-to-drag ratio (L/D) of 0.5 provides sufficiently large entry corridor depth at velocities up to 55,000 fps to allow safe entry within capability of existing guidance and navigation systems; increase in vehicle slenderness to reduce radiant heating results in higher surface Reynolds numbers, thus increasing possibility of boundary-layer transition and attendant increase in convective heating; experimental data for ablative heat shield of Apollo command module imply that existing heat shields can provide efficient thermal protection for planetary return missions. (02636)
Manned earth entry at hyperbolic velocities
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 9
1968
7 pages
Aufsatz (Zeitschrift)
Englisch
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Manned earth entry at hyperbolic velocities.
AIAA | 1968
|Look at manned entry at circular to hyperbolic velocities
Engineering Index Backfile | 1963
|Earth entry at hyperbolic velocities
AIAA | 1968
|