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针对利用喷气执行机构实现航天器姿态机动时柔性附件的振动抑制问题,以期望的姿态指向精度及稳定度为约束,提出了需要抑制的系统模态阶次选取准则。仿真验证模型由绕单轴旋转的中心刚体及柔性附件组成,应用拉格朗日法建立适用于不同附件位置的系统动力学方程,利用准则设计了常幅值分力合成控制力矩。仿真结果验证了所提出准则的有效性,并表明:在姿态机动前若能适当调整柔性附件的位置,将便于分力合成控制器设计,易于获得较高的姿态指向精度及稳定度,且利于减少喷气次数。
In order to suppress the vibration of flexible attachments when the attitude of the spacecraft is maneuvered by the jet actuator, the order of system modal selection is put forward based on the desired attitude pointing accuracy and stability constraints. The simulation model consists of a rigid body centered around a single axis and a flexible attachment. The system dynamic equations for different attachment positions are established by Lagrange method. The simulation results verify the validity of the proposed criterion and show that if the position of the flexible attachment can be adjusted properly before the maneuvering of the maneuver, it will be easier for the component controller to design, which will make it easier to obtain high attitude pointing accuracy and stability, Reduce the number of jets.