The invention provides a satellite position keeping control method and device, and relates to the technical field of satellite control, and the method comprises the steps: a first determination step: determining the working parameters of a satellite thruster in a position keeping ignition period; a second determination step of determining a correction threshold of the disturbance torque of the target satellite thruster based on the working parameters; a third determination step of determining target parameters based on the correction threshold of the disturbance torque of the target satellite thruster, the target parameters including the ratio of the number of position keeping ignitions to the number of position correction ignitions, and the ignition duration of position correction ignition; and a control step: sending the target parameters to a satellite thruster, so that the satellite thruster optimizes the attitude and angular momentum of the satellite by using the target parameters, and the technical problems that in the prior art, when the position of the satellite is kept and controlled, measurement and control personnel need to carry out more manual operation, and more time is consumed are solved.
本发明提供了一种卫星位置保持的控制方法和装置,涉及卫星控制的技术领域,包括:第一确定步骤,确定卫星推力器在位置保持点火期间的工作参数;第二确定步骤,基于工作参数,确定出目标卫星推力器的干扰力矩的修正阈值;第三确定步骤,基于目标卫星推力器的干扰力矩的修正阈值,确定出目标参数,其中,目标参数包括:位置保持点火次数与位置修正点火次数的比例,位置修正点火的点火时长;控制步骤,将目标参数发送给卫星推力器,以使卫星推力器利用目标参数对卫星的姿态与角动量进行优化,解决了现有技术在对卫星进行位置保持控制时需要测控人员进行的人工操作较多,耗费较多的时间的技术问题。
Satellite position keeping control method and device
一种卫星位置保持的控制方法和装置
2021-04-06
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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