COPLANAR 2-IMPULSE RENDEZVOUS IN GENERAL ELLIPTIC ORBIT WITH DRAG

The numerical solution of the two-impulse terminal rendezvous for the formation flying of two spacecraft with different ballistic coefficien ts in general elliptic orbit is presented. The motion of the passive v ehicle is described by the inverse-square gravitational field of the p rimary body and by atmospheric drag. The center of a rotating referenc e frame is attached to this vehicle, and the motion of the active mane uvering vehicle is described relative to this accelerating frame. This allows for the solution of the exact, arbitrary duration two-impulse rendezvous problem, with both vehicles continuously subject to drag in their respective orbits during the maneuvering period, meaning betwee n the application of the first or initiating impulse, and the final or terminating impulse which achieves the desired rendezvous. Examples o f rendezvous which bring the vehicles to close proximity for various t ransfer durations are presented to support this analysis.