CE-4中继卫星使命轨道维持与动量轮卸载联合控制方法

针对嫦娥四号中继卫星动量轮频繁喷气卸载对其使命轨道Halo轨道的扰动问题，定性分析了卫星角动量累积规律和动量轮卸载对使命轨道构型的影响，给出了动量轮卸载前后角动量变化量与喷气卸载等效速度增量的关系，在角动量卸载预测的基础上，提出了一种使命轨道维持与动量轮卸载联合控制方法，通过偏置维持控制目标抵消控后动量轮卸载影响，达到延长轨道维持控制周期和节省推进剂的目的，给出了控制目标偏置量的求解方法。工程应用结果验证了方法的有效性。

A Combined Control Method of Chang’e-4 Relay Satellite’s Mission Orbit Keeping Maneuver and Momentum Wheel Unloading#br#

To solve the problem of the unexpected disturbance to the Halo orbit of the Chang’e-4 relay satellite caused by the frequent momentum wheel unloading under the control of thrust, the influence of the momentum wheel unloading on the mission-orbit configuration and momentum cumulative rules are analyzed qualitatively, and the mathematic relationship between the amount of momentum change and velocity increment is given. Based on the prediction of the momentum unloading time and variation, a combined control method of the mission orbit-keeping maneuver and momentum wheel unloading is put forward. Through optimizing the configuration-keeping objective offset of the Halo orbit, a goal of eliminating the adverse effects of the momentum wheel unloading on the orbit configuration is achieved, with a longer orbit-keeping period and less fuel consumption, and besides a solution method of the control objective offset is given. The experimental results on the measured profiles verify the validity and feasibility of the proposed method.