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针对空间飞行器柔性附件低频振动衰减缓慢降低系统稳定性和可靠性的问题,以带有驱动机构的太阳能电池翼为例,不增加额外机构,提出了以驱动机构为作动器、电池翼与驱动机构约束扭矩为目标的振动控制方法。推导了模态坐标表示的电池翼振动的状态方程,选择第一阶模态描述电池翼弯曲振动并设计反馈控制律。以钢质弹性直尺为模型,通过数值仿真验证了该方法的有效性。
Aiming at the problem that the low-frequency vibration decay of spacecraft flexible accessories slows down the stability and reliability of the system slowly, taking the solar cell wing with driving mechanism as an example, an additional mechanism is added without any additional mechanism. A driving mechanism, a battery wing and a driving Mechanism restraining torque as the target vibration control method. The equation of state of battery wing vibration expressed by modal coordinates is deduced. The first order mode is chosen to describe the bending vibration of battery wing and the feedback control law is designed. The model of steel elastic ruler is used to verify the effectiveness of the method through numerical simulation.