The invention relates to the technical field of spacecraft attitude orbit control, in particular to a joint position keeping control method and device under the condition of centroid deviation. The method comprises the following steps: determining the direction in which a satellite drifts due to tangential thrust generated by coplanar installation of electric thrusters and the semi-major axis variation of the satellite in a position keeping control period when the centroid of the whole satellite deviates by 1mm every time; determining a target offset direction and a target offset of the center of mass of the whole satellite according to a drift direction of flat longitude of the satellite caused by perturbation acceleration and a semi-major axis variation of the satellite in a position keeping control period under the action of earth perturbation force; based on the target offset direction and the target offset, adjusting the whole satellite centroid position of the satellite; after a satellite is fixed in an orbit, when the electric thrusters installed in a coplanar mode are used for autonomously conducting south-north position keeping control in each operation day, due to the fact that the offset of the mass center of the whole satellite can generate tangential thrust at the same time, the south-north position keeping control is completed, and meanwhile an east-west position keeping control task is completed.
本发明涉及航天器姿态轨道控制技术领域,特别涉及一种质心偏差情况下的联合位置保持控制方法和装置。方法包括:确定整星质心每偏离1mm时,共面安装电推力器产生的切向推力致使卫星漂移的方向以及卫星在位置保持控制周期内的半长轴变化量,以基于摄动加速度致使卫星平经度的漂移方向和地球摄动力作用下卫星在位置保持控制周期内的半长轴变化量,确定整星质心的目标偏移方向和目标偏移量;基于目标偏移方向和目标偏移量,调整卫星的整星质心位置;卫星在轨定点后,利用共面安装电推力器在每一个操作日自主进行南北位置保持控制时,由于卫星整星质心的偏移可以同时产生切向推力,故而完成南北位置保持控制的同时也完成了东西位置保持控制任务。
Joint position keeping control method and device under centroid deviation condition
质心偏差情况下的联合位置保持控制方法和装置
2024-02-13
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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