An orbiter entry guidance system for the hypersonic phase of reentry lead to a concept which is partially different from that of the U.S. Shuttle. The addressed flight regime ranges from the initial atmospheric penetration point down to an Earth relative velocity of about 700 m/s at which point the control is transferred to the terminal area energy management system. A guidance concept is embedded in a closed loop simulation environment, which enables an investigation of its performance and especially its robustness with regard to various assumed errors and perturbations, is described. The guidance concept presumes the presence of precalculated nominal trajectories.
Guidance and Control for Re-Entry Vehicles
1991
6 pages
Report
No indication
English
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