航天器喷气姿态机动分力合成抑制模态选取准则

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。

Selection Criteria of Component Synthesis Vibration Suppression Mode Order for Spacecraft Attitude Maneuver with Reaction Jet Actuators

Aiming at the problem of Component force Synthesis Vibration Suppression(CSVS) by using the jet actuator to realize attitude maneuver, and taking the expected attitude pointing accuracy and stability as constraint conditions, a selection criteria is proposed to select some orders of the system vibration mode which indeed need to suppress. The simulation test model is consist of the center rigid body rotated around a single axis and flexible accessories, the Lagrange method is used to establish dynamics equations applicable to different positions of attachment, then the selection criteria is applied to design constant amplitude component synthesis control moment.Simulation results prove that the selection criteria is effective, and if the flexible accessories are adjusted to an appropriate position before attitude maneuver, the control design is more simple, and easier to gain higher attitude accuracy and stability, as well has the advantages of jet fewer.