The problem of designing a manned space vehicle which must survive entry into the earth's atmosphere is discussed from the systems point of view. In the design of such a vehicle peak deceleration loads become an important consideration. This aspect of the problem together with the aerodynamic heating and landing point dispersion factors is considered for two classes of re-entry bodies: (1) returning low-altitude satellite, and (2) vehicles which re-entry at or near escape velocity such as circumlunar vehicles. Finally, the heat shielding problem is presented in detail along with some solutions. (Author)
Descent Trajectories for Manned Space Vehicles
1958
1 pages
Report
Keine Angabe
Englisch
Study of powered-descent trajectories for manned lunar landings
TIBKAT | 1964
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Engineering Index Backfile | 1963
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