航天器微振动一体化建模与控制研究

Integrated Micro-vibration Modeling and Control Investigation of Spacecrafts

为实现航天器载荷的高精高稳控制,研究了航天器微振动一体化集成建模与控制方案。首先,根据航天器典型微振动源构建航天器本体微振动的动力学与控制集成模型,并对其进行姿态控制仿真。然后进一步构建包含载荷-本体隔振界面的航天器微振动集成动力学与控制模型,为比较分析被动控制隔振与主被动控制隔振,分别仿真了对载荷被动隔振以及主被动混合隔振两种方案下的姿态控制。结果证实主被动控制混合隔振可有效提高载荷姿态精度和稳定度2个数量级,实现了航天器载荷的高精度高稳定度控制。

The integrated micro-vibration modeling and control scheme are thus investigated to achieve high accuracy and high stability control of the spacecraft payload. At first, the integrated model including the dynamics and control of the spacecraft body containing typical vibration sources is derived. The attitude control simulation of the spacecraft is implemented. Then, using the proposed model of the spacecraft body, the integrated model of the whole spacecraft containing the payload-body vibration isolator is derived. To compare the performance of the passive vibration isolation and passive-active hybrid isolation, the attitude control of payload is simulated. The simulation results confirm that the passive-active hybrid isolation improves the accuracy and stability of the payload attitude control by two orders. The high accuracy and high stability control of the spacecraft payload is thus achieved.