United optimization control of multi-paramters for the complex and the spacecraft´s orbits

Aimed at the problem of multi-paramters control for the complex and the spacecraft´s orbits, the equations of the longitude of ascending anode, the local orbit height, the orbit eccentricity and even the time conjunction between of the controls are established. Based on the pertinence of orbit objectives and flight time and the characters of the complex´s quite long flight and the spacecraft´s quite short flight, the united optimization control stragety which the complex orbit´s control for the longitude of ascending node and the orbit eccentricity and the spacecraft orbit´s control for the brake point height is instituted. With the high precise orbit dynamics model of the twin-body and the single body, the iteration computation flow is designed. Simulation results shows that the method and the strategy of united optimization control of orbit multi-paramters are effective with rapid convergence and high precise and are applicable for engineering application.