RCD太阳帆航天器人工平动点轨道保持与控制

针对航天器平动点轨道保持问题,研究了含有反射率控制设备(RCD)的太阳帆航天器在日地系共线人工平动点处的轨道保持与控制,同时降低因频繁改变航天器姿态所带来的振动问题。首先,基于太阳帆圆型限制性三体问题,计算了RCD型太阳帆人工平动点位置,给出了太阳帆共线人工平动点三阶Halo轨道,并将其作为参考轨道;然后,将太阳帆动力学方程线性化,采用跟踪控制输出的方法对线性模型进行控制;最后,通过合理选择控制变量矩阵,将控制律代入非线性模型中进行轨道保持控制。仿真结果表明,通过控制RCD太阳帆反射率设备参数及姿态角,实现了长时间的Halo轨道保持,同时大幅减小了太阳帆姿态角的改变,从而减小了帆面振动,为太阳帆航天器长期轨道任务的实现提供了良好的理论依据。

Orbit keeping and control of solar sail spacecraft with RCD on artificial libration points

For problem of the orbit keeping at libration point, the orbit keeping and control of the solar sail spacecraft with reflectivity control device(RCD) at collinear artificial libration point of Sun-Earth system was studied, and the vibration of spacecraft which comes from the frequently change of attitude angle was decreased. Firstly, based on the solar sail circular restricted three-body problem, the position of the artificial libration points of the RCD solar sail were calculated, and the third-order Halo orbit expression of the collinear artificial libration points of the solar sail was given as the reference orbit. Then, the dynamics equation of the solar sail was linearized to establish the equation of state, and the linear model was controlled by the linear quadratic regulator of the tracking control output. Finally, the control law was substituted into the nonlinear model to maintain the orbit by reasonably selecting the control variable matrix. The simulation results showed that the Halo orbit was maintained for a long time by changing the reflectivity parameters and the attitude angle. At the same time, this method can reduce the change of the attitude angle of the solar sail, thus reducing the vibration of the solar sail, which has a good theoretical value for the long-time orbit mission of the solar sail spacecraft.