The invention relates to an angular momentum control strategy for four oblique configuration flywheels of a zero momentum satellite, and belongs to the technical field of spacecraft attitude control. The technical problem that in the prior art, an angular momentum control scheme of a four-inclined-configuration flywheel is low in accuracy is solved. According to the zero momentum satellite four-oblique configuration flywheel angular momentum control strategy, firstly, angular momentum unloading is carried out, and the satellite angular momentum is unloaded to be close to zero momentum; judging whether to calculate the angular momentum bias control moment of the flywheel or not according to the current angular momentum deviation condition of the flywheel; calculating an attitude control moment according to the current attitude deviation; angular momentum bias control torque and attitude control torque are comprehensively considered as flywheel control output torque. According to the control strategy, in the flywheel angular momentum bias process, the angular momentum bias control torque and the attitude control torque are considered at the same time, smooth execution of the angular momentum bias control torque is guaranteed, and attitude stability in the execution process is also guaranteed.
本发明涉及一种零动量卫星四斜装构型飞轮角动量控制策略,属于航天器姿态控制技术领域。解决了现有技术中四斜装构型飞轮的角动量控制方案精确度低的技术问题。本发明的零动量卫星四斜装构型飞轮角动量控制策略,首先进行角动量卸载,将卫星角动量卸载至零动量附近;然后根据飞轮当前的角动量偏差情况判断是否进行飞轮角动量偏置控制力矩计算;然后根据当前姿态偏差计算姿态控制力矩;综合考虑角动量偏置控制力矩为与姿态控制力矩作为飞轮控制输出力矩。本发明的控制策略在飞轮角动量偏置过程中同时考虑了角动量偏置控制力矩的与姿态控制力矩,既保证了角动量偏置控制力矩的顺利执行,又保证了执行过程中姿态稳定。
Angular momentum control strategy for four-oblique-configuration flywheel of zero momentum satellite
一种零动量卫星四斜装构型飞轮角动量控制策略
2024-10-22
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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