航天器姿态和振动的拉索控制模型

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。

Cable control model for spacecraft attitude and vibrations

In practice,the attitude control of a spacecraft and the vibration control of its flexible components are designed separately and operated in sequence,which increases the running time.This paper focuses on simultaneous control of both the attitude and vibrations of a spacecraft.A coupled-flexible-rigid space structure was modeled using the modal superposition method with a cable structure used as the actuator with the control law designed using linear quadratic Gaussian(LQG) theory.Simulation results show that the spacecraft attitude deviation and the flexible component vibrations are effectively attenuated for various perturbations.The effect of cable carrier counterforce on the system stability was analyzed to show that neglect of the counterforce leads to control system instability.