太阳帆动力学建模与姿态控制

Research on solar sail dynamic modeling and attitude control

对基于控制杆的太阳帆航天器,对其结构进行合理简化,应用矢量力学原理建立了太阳帆航天器刚柔耦合动力学方程,通过求解太阳帆航天器支撑杆的非约束模态,进而给出太阳帆航天器动力学方程的求解方法.结合运行于超地球同步转移轨道上的太阳帆航天器的偏航轴对地定向任务,设计了基于控制杆的太阳帆航天器俯仰轴Bang-Bang PD控制器.数值仿真结果表明,所设计的控制器可以在700 s内实现考虑太阳帆航天器结构振动的偏航轴对地无偏差定向任务.

For a solar sail spacecraft with a control boom, the structure was reasonably simplified, and a vector me- chanics method was adopted to deduce rigid-flexible coupling dynamic equations for the solar sail. The solutions of dynamic equations for the above solar sail were achieved by solving the unconstrained modes of the supporting beams. A proportional-derivative （PD） controller considering Bang-Bang control strategies based on a control boom was designed combining the problems of yaw axis earth-pointing issue of solar sail on super-synchronous transfer or- bit. Numerical simulations indicate that the designed controller, is capable by the control boom of achieving the yaw axis earth-pointing task considering the vibration of the solar sail within 700 seconds.