挠性多体卫星姿态动力学与控制

Attitude dynamics and control of a flexible multi-body satellite

三轴稳定卫星挠性附件的弹性振动和刚性部件的转动与卫星的姿态运动构成耦合的强非线性系统,因此须设计有效的控制律。该文研究了采用反作用飞轮作为执行机构、带有柔性附件和刚性转动部件的整星零动量三轴稳定卫星的姿态解耦控制问题。导出了卫星的多体系统动力学方程,并给出了部分线性化的形式。进一步利用反馈线性化方法将非线性耦合系统解耦,然后对线性化的系统模型进行状态反馈解耦和极点配置。数值仿真结果表明,该文所设计的控制方法具有很高的姿态控制精度和稳定度。

Very accurate control systems are needed to control the structural vibrations and the rigid body rotation of a three-axis stabilized satellite which are coupled to the satellite attitude movements. This paper analyzes attitude decoupling control of a three-axis stabilized satellite in a zero-momentum state with reaction wheels. The non-linear dynamic equations for the multi-body satellite system were linearized with the feedback linearization method used to decouple the nonlinear system into a linearized control system, A state feedback deeoupling law and a pole assignment law were then designed for the linearized control model. Numerical simulation results show that the method is precise with highly stable attitude control.