The parameter defining the Keplerian phase of the reentry mission of a winged vehicle descending from circular low Earth orbit into atmosphere at 120 km altitude was studied. Entry parameter variations with deorbiting maneuver characteristics, and their sensitivities were analyzed.
Study on Reentry Guidance and Control. Volume 3: Reentry Trajectory Simulation
1988
502 pages
Report
Keine Angabe
Englisch
Trajectory optimization and guidance strategies for reentry
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