组合体与飞船联合轨道维持

通过组合体与飞船联合轨道维持解决了组合体和飞船轨道多特征参数的控制问题。建立了升交点经度、轨道高度和偏心率的控制方程以及基于时间关联特性的升交点赤经和制动点高度耦合控制方程和偏心率保持的双冲量耦合控制方程。结合组合体与飞船的飞行特点，制定了组合体轨道维持实现升交点赤经和轨道偏心率以及飞船轨道维持实现制动点高度的联合控制策略。耦合控制方程使得组合体和飞船轨道维持的控制量分配合理，融合了各次控制之间存在的耦合影响，设计了联合轨道维持策略迭代计算流程。基于神舟九号交会对接飞行过程，通过多组仿真算例校验了组合体与飞船轨道多特征参数的联合优化控制，具有较好的工程应用价值。

The Complex’s and the Spacecraft’s United Orbit Maintenances

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.