Motion in general elliptic orbit with respect to a dragging and precessingcoordinate frame

The full set of second-order nonlinear differential equations describing th e exact motion of a spacecraft subject to drag and oblateness perturbations in general elliptic orbit, relative to a rotating reference frame which dr ags and precesses exactly as a given spacecraft attached to its center is d erived. This attached spacecraft is itself flying a general elliptic orbit and can be considered as the passive or nonmaneuvering vehicle. The unavera ged form of the J(2) acceleration is used for both vehicles leaving this ob lateness perturbation position dependent for more exacting calculations. Th ese equations can be effectively put to use in calculating by an iterative scheme, the impulsive rendezvous maneuvers in elliptic orbit around the Ear th or those planets that are either atmosphere bearing or have a dominant s econd zonal harmonic, or both.