带滑块的太阳帆航天器刚柔耦合动力学建模与姿态控制

Dynamic Modeling and Attitude Control of Rigid-Flexible Coupling for Solar Sail Spacecraft with Slider Controller

为了对滑块控制的太阳帆航天器的姿态控制进行研究,利用动量矩定理建立了太阳帆的刚柔耦合动力学方程,并利用非约束模态方法,求得了可解的控制学方程,在此基础上提出了90°定向任务这一新的姿态控制任务情景。以90°定向任务为切入点,对带滑块的太阳帆航天器姿态-控制非线性耦合的特点进行了讨论,并针对其给出了一种能够适应这种非线性耦合特征的变增益PD控制器。对90°定向任务进行了仿真,结果表明,当姿态角接近90°时,姿态-控制器非线性耦合程度较强,定增益PD控制器控制效果差。此时,变增益PD控制能够对非线性特性凸显,对定增益PD控制难以实现的90°定向任务进行精确控制,在可接受的控制时间内将姿态角定向为90°。

In order to study the attitude control of solar sail spacecraft controlled by sliding block,the rigid flexible coupling dynamic equation of solar sail is established,and the solvable control equation is obtained by using the unconstrained mode method.On this basis,a new attitude control mission named 90°orientation mission is proposed.Taking the 90°orientation mission as the breakthrough point,the nonlinear coupling characteristics of attitude control of solar sail spacecraft with slider are discussed,and a variable gain PD controller which can adapt to the nonlinear coupling characteristics is proposed.The simulation results show that when the attitude angle is close to 90°,the nonlinear coupling degree of attitude controller is high,and the control effect of constant gain PD controller is poor.At this time,the variable gain PD controller can accurately control the 90°orientation task which is difficult to achieve by the constant gain PD controller,and the attitude angle can be oriented to 90°within the acceptable control time.