Equations of powered rocket ascent and orbit trajectory

Details Equations of powered rocket ascent and orbit trajectory Equations of powered rocket ascent and orbit trajectory

May 1979

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979nrl..repts....r&link_type=abstract

Final Report Naval Research Lab., Washington, DC. Communication Sciences Div.

Physics

Ascent Trajectories, Elliptical Orbits, Spacecraft Trajectories, Earth (Planet), Equations Of Motion, Launch Vehicles

Scientific paper

Equations of rocket and satellite dynamics are obtained at various levels of approximation and make possible analyses of powered rocket ascent, orbit injection, and subsequent orbital motion. Rocket and satellite trajectory are specified by these equations, which include the effects of earth's rotation and curvature. Various analysis techniques are given, so that the investigator can choose the simplest one suited to his needs. In the process, material not readily available is presented, and some problems of ambiguity and inaccuracy in standard references are resolved.

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