Author(s)Ward, Jr, James A
KeywordsSpacecraft Trajectories and Reentry
DATA PROCESSING EQUIPMENT
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AbstractDue to perturbative forces acting on a near earth satellite, the associated classical Keplerian orbital elements vary with time. These variations are divided into secular, short period and long period. The mathematical equations expressing these variations are presented without derivation along with numerical examples. A discussion of the practical applications of these variations to trajectory generation and orbit determination is included.
Prepared in cooperation with RCA International Service Corp. , Patrick AFB, FL, Missile Test Project.