Fast autonomous guidance algorithm for spacecraft far range rendezvous phasing

A fast autonomous guidance algorithm was designed based on classical orbital elements for spacecraft far range rendezvous phasing in near-circular orbit. For arbitrary initial argument of latitude difference, the phasing maneuver was divided into three stages-the initial orbit, the phasing orbit and the adjusting orbit according to the relationship of argument of latitude difference and semi-major axis difference. Coplanar orbital correction and phase maneuvering were done in the initial orbit. In the phasing orbit, the argument of latitude difference was adjusted naturally because of the semi-major axis difference, and then the orbit maneuver from the phasing orbit to the adjusting orbit was implemented. In the adjusting orbit, the apogee altitude and the apogee altitude of chase spacecraft are adjusted to the same as those of target spacecraft at first. Furthermore, a coplanar orbital correction was done again to eliminate the cross-track difference. All orbital maneuvers were given as guidance impulses and implemented in the orbital special points. Precise orbital simulation results show that the fast autonomous guidance algorithm for far range phasing maneuvers is feasible.