A space launcher that is recoverable was studied. Possible configurations were investigated and dimensioning parameters were identified. Analysis centered on design of a two-stage vehicle in a winged or ballistic configuration. The launch vehicle mission was defined as injection into low Earth orbit of a 10,000 kg payload. Results concern choice of propulsion system as well as ascent and descent trajectories (including implications for thermal protection).
Future Launching Systems
1981
71 pages
Report
Keine Angabe
Englisch
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