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Vibration suppression of flexible spacecraft during attitude maneuver using CMGs

机译：使用CMG抑制挠性航天器在姿态操纵过程中的振动

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摘要

AbstractIn this paper, control moment gyroscope (CMG) system is employed to suppress vibration of flexible spacecraft during attitude maneuver. Direct modal force generated by CMGs is exerted to elastic dynamics due to interaction between CMGs and flexibilities of structure. A novel control strategy based on a modal force compensator is proposed, which is simple and efficient to reduce vibration during attitude maneuver. The proposed modal force compensator avoids exciting vibration by the means of canceling out disturbance input to elastic dynamics using modal force generated by CMGs. No modal information is required in the modal force compensator. A concept named as modal force singularity is introduced and analyzed in depth. A restriction on gimbal angles is developed to avoid modal force singularity. Subsequently, a steering logic based on pseudo-inverse is proposed to allocate modal force commands without introducing force errors. Numerical simulations are presented to show the effectiveness of the proposed approaches.
机译： 摘要 在本文中，控制力矩陀螺仪（CMG）系统用于抑制姿态操纵期间挠性航天器的振动。由于CMG之间的相互作用和结构的柔韧性，CMG产生的直接模态力会施加到弹性动力学上。提出了一种基于模态力补偿器的新型控制策略，该控制策略简单有效地减小了姿态操纵过程中的振动。所提出的模态力补偿器通过使用CMG产生的模态力来抵消输入到弹性动力学中的干扰，从而避免了激振。模态力补偿器中不需要模态信息。引入了称为模态力奇异性的概念，并对其进行了深入分析。为了避免模态力奇异性，对万向架角度进行了限制。随后，提出了一种基于伪逆的转向逻辑来分配模态力命令而不会引入力误差。数值仿真表明了所提方法的有效性。

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