Abstract: According to the target spacecraft′s orbit height and the chaser spacecraft′s orbit height, the design method of the target′s initial phase for the rendezvous orbit was presented. The mathematical models of the target′s rendezvous orbit control were established, which included the model of the coplanar phase and the model of the multi objective parameters to solve the target′s orbit phase, height and eccentricity. Based on the target′s phasing time analysis of orbit determination error, orbit control error and orbit prediction error, the strategy of the target′s phasing orbit maneuver was developed. Simulation results indicate that the target′s rendezvous orbit is obtained to meet the requirements of the objective orbit and the optimization principles of phasing control delta velocity is verified. Even the difference of the normal coplanar and the virtual coplanar is compared. The proposed model, control strategy and analysis methods are applicable to the target′s rendezvous orbit design and control implementation.

Key words: Rendezvous, Docking, Orbit control, Target spacecraft