Abstract:

The problem of multi parameter control for the complex’s and the spacecraft’s orbits is solved by use of the complex and the spacecraft united orbit maintenances. The control equations of the right ascension of ascending node, the orbital altitude and the orbital eccentricity are established. Two coupled control equations based on the flight time, one for the longitude and the braking point altitude and the other for the double impulses for the orbit eccentricity are designed. Based on the flight characteristics of the complex and the spacecraft, an united control strategy is instituted for the complex orbit control of the right ascension of ascending node and the orbit eccentricity and the spacecraft orbit control of the braking point altitude. The complex’s and the spacecraft’s orbit maintenances delta velocities are rationalized to combine with the coupled effect of the controls. The iterative computation flow of the united orbit maintenance is designed. Simulation results based on the Shenzhou 9 rendezvous and docking mission show that the method and the strategy are effective and are applicable for engineering application.