The embodiment of the invention discloses an oblique mounting attitude control flywheel angular momentum optimal distribution method. In one specific embodiment, the method comprises the following steps: establishing an angular momentum envelope of the flywheel configuration according to an installation matrix of a flywheel system in the flywheel configuration; the target limit angular momentum of each flywheel at the current moment is solved according to the real-time rotating speed of each flywheel in the flywheel configuration; calculating the optimal distribution control moment of each flywheel according to the deviation between the current angular momentum and the target limit angular momentum of each flywheel in the flywheel configuration; and superposing the optimal distribution control moment on the attitude control moment to obtain a control instruction moment of each flywheel so as to realize attitude control of the satellite and optimal distribution of the angular momentum of the flywheels. According to the method, the rotating speed saturation of the single flywheel before the flywheel set reaches the target limit angular momentum in the control process is avoided, so that the reduction of the satellite attitude control precision caused by the rotating speed saturation of the single flywheel is avoided, and the control capability of the flywheel set is utilized to the maximum extent.
本发明实施例公开一种斜装姿态控制飞轮角动量优化分配方法。在一具体实施方式中,该方法包括:根据飞轮构型中飞轮系统的安装矩阵建立飞轮构型的角动量包络体;根据飞轮构型中各飞轮的实时转速求解当前时刻各飞轮的目标极限角动量;根据飞轮构型中各飞轮当前角动量与目标极限角动量的偏差计算各飞轮优化分配控制力矩;将优化分配控制力矩叠加在姿态控制力矩上,得到各飞轮的控制指令力矩,以实现卫星的姿态控制和飞轮角动量的优化分配。本发明避免在控制过程中飞轮组未达到目标极限角动量前单个飞轮转速饱和,从而避免单飞轮转速饱和导致的对卫星姿态控制精度下降,最大化的利用了飞轮组的控制能力。
Oblique installation attitude control flywheel angular momentum optimal distribution method
一种斜装姿态控制飞轮角动量优化分配方法
2023-09-12
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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