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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。
In order to realize the high precision and stability control of spacecraft payloads, integrated modeling and control schemes of spacecraft micro-vibration are studied. First of all, based on the typical micro-vibration source of spacecraft, the dynamics and control integration model of the ontology micro-vibration of the spacecraft is constructed and the attitude control simulation is carried out. Then the micro-vibration integrated dynamics and control model of the spacecraft with load-body vibration isolation interface are further constructed. In order to comparatively analyze the passive control vibration isolation and the active and passive control vibration isolation, the passive vibration isolation and active-passive vibration isolation Attitude control under two scenarios. The results show that the hybrid active and passive vibration control can effectively improve the attitude accuracy and stability of the load by two orders of magnitude, and realize the high-precision and high-stability control of the spacecraft payload.