Space shuttle trajectory-shaping optimization considering the vehicle's thermal environment and the resulting requirements of the thermal protection system (TPS) are discussed. Optimization studies have been conducted yielding results which are generally applicable to shuttle orbiters and are independent of evolution and redirection of the space shuttle program. Two investigations of optimal trajectory shaping, with different methods of considering the thermal environment are presented.
Orbiter entry trajectory considerations
1972-02-01
Conference paper
No indication
English
Allowable Trajectory Variations for Space Shuttle Orbiter Entry-Aeroheating CFD
British Library Conference Proceedings | 2008
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