PDF document - Orbital and Celestial Mechanics Website

dhh dt2p s 2wncos Ldkk dt2p s 2wnsin L2dL w 1 pL p hsin L k cos Lndtp w where r, t , nare non-two-body perturbations in the radial, tangential and normal directions,respectively. The radial direction is along the geocentric radius vector of the spacecraft measuredpositive in a direction away from the gravitational center, the tangential direction is perpendicular to thisradius vector measured positive in the direction of orbital motion, and the normal direction is positive inthe direction of the angular momentum vector of the spacecraft’s orbit.The equations of orbital motion can also be expressed in vector form as follows:wheredyy A yP bdt2 p p 0 0 w p p 1p g sin L w 1cos L f h sin L k cos L w w p p 1p f cos L w 1sin L g h sin L k cos L w wA 2p s cos L0 0 2w2p s sin L 0 0 2wp 1 0 0 h sin L k cos L wandb 0 0 0 0 02w p p TThe total non-two-body acceleration vector is given bypage 18