组网卫星电推进自主轨道保持方法

Autonomous Orbit Keeping for Satellite Constellations Based on Electric Propulsion

以某对地观测星座任务为背景,对基于电推进的组网卫星自主轨道保持控制方法进行研究。由地面进行标称轨道递推并定期上注,星上考虑地球非球形J2项摄动进行本星和标称星拟平均轨道参数递推,采用单边极限环方法进行面内相位保持控制。针对长期运行在对日定向模式的倾斜轨道且固定太阳翼卫星,考虑能源、程控任务、轨道偏心率等约束,设计了卫星自主轨控实施方案。以高精度轨道摄动模型进行数学仿真,验证了算法的有效性。

The autonomous orbit keeping method for satellite constellations by means of electric propulsion is studied. Nominal orbit recursion is carried out from the ground and injected regularly. The quasi-mean orbit parameters of the local satellite and the reference satellite are recursed,considering the non-spherical J2 perturbation of the earth,and intra-planar phase keeping is controlled with the single side limit cycle method. A satellite autonomous orbit control scheme is designed for a fixed solar wing satellite running in the solar-oriented mode for a long time,considering the constraints of the energy,program control task,and orbit eccentricity. The effectiveness of the algorithm is verified with a high precision orbit perturbation model.