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在工程中,航天器的姿态控制和柔性部件振动控制一般采用分开设计和分时段执行,这样增加了航天器的控制时间。该文采用拉索结构作为控制作动器,用模态叠加法对航天结构模型进行刚柔耦合建模,并用线性二次型最优控制方法设计一个控制算法,对航天器姿态及其柔性部件同时进行控制。仿真结果显示,航天结构在各种激励下产生的姿态漂移和柔性附件振动同时得到了快速稳定的抑制。针对拉索控制的特点,分析了拉索的支座反力对控制系统的影响。结果表明,在结构建模中如果不考虑支座反力,将会导致控制系统不稳定。
In engineering, attitude control of spacecraft and control of flexible components are generally implemented separately and sub-periods, which increases the control time of the spacecraft. In this paper, the cable structure is used as the control actuator, and the modal superposition method is used to model the rigid-flexible coupling of the aerospace structure model. A linear quadratic optimal control method is used to design a control algorithm to control the aerospace attitude and its flexible components At the same time control. The simulation results show that the attitude of the aerospace structure under various stimuli and the vibration of the flexible attachment are rapidly and stably restrained at the same time. According to the characteristics of cable control, the influence of cable bearing reaction on the control system is analyzed. The results show that if the bearing reaction force is not considered in the structural modeling, the control system will be unstable.