多目标多约束组合体与飞船轨道维持优化

针对天宫二号/神舟十一号任务组合体运行与飞船返回要求，建立了升交点经度、轨道偏心率、指定时刻轨道高度及速度倾角等多目标特征参数的控制方程；根据组合体至飞船撤离准备各阶段的飞行特点，分析了近圆轨道偏心率中长期演化情况以及飞船返回双脉冲控制量随控制时间的变化规律，提出了通过两次组合体与飞船联合规划来满足不同约束的控制策略；根据撤离后飞船、天宫以及伴星的相对运动关系研究了结合规避控制的飞船双脉冲维持优化控制方案。最后依据神舟十一号任务的飞行过程，设计算例验证了该方法的有效性，具有较好的工程应用价值。

Multi Target and Multi Constraint Optimization of Orbit Maintenance of Complex and Spacecraft

The longitude of ascending node, the orbital eccentricity, the braking point’s altitude and flight path angle are required in the orbit maintenance of the TG-2/SZ-11 mission. Despite of the multiple targets, the aim of decreasing the collision risk between SZ-11, TG-2 and its concomitant satellite greatly increases the complexity of the maintenance. In this paper, the control equations of the multiple targets in the mission are established. Two important regularities are analyzed according to the flight characteristics, one for the evolution of the eccentricity of the near-circular orbit and the other for the rules of velocity increment of spacecraft’s double-impulse control varying with the impulse time. Then, a multi-target and multi-constraint optimization strategy is instituted. The simulation results based on the TG-2/SZ-11 mission show that the method and the strategy are effective and are applicable for engineering applications.