Maneuvers in which orbital plane of earth satellite is changed by means of aerodynamic forces during one or more skips into and out of atmosphere are analyzed; characteristic velocities required of rockets to deflect vehicle into atmosphere and to reaccelerate it to orbital speed after leaving atmosphere are calculated as functions of change in inclination lift-drag ratio, and entry angle, and compared with characteristic velocities required for purely extra-atmospheric rocket maneuvers.
Change of satellite orbit plane by aerodynamic maneuvering
J Aerospace Sciences
Journal of the Aero/Space Sciences ; 29 , n 3
1962
10 pages
Aufsatz (Zeitschrift)
Englisch
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