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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。
The elastic vibration of the flexible attachment of the three-axis stable satellite and the rotation of the rigid component form a strong nonlinear system coupled with the attitude movement of the satellite, so an effective control law needs to be designed. In this paper, the problem of attitude decoupling control of a full-scale, zero-momentum, three-axis stabilized satellite with a reactive flywheel as an actuator, a flexible attachment and a rigid rotating part is studied. The multi-body system dynamics equations of satellite are derived and some linearized forms are given. The feedback linearization method is further used to decouple the nonlinear coupling system, then the state feedback decoupling and pole placement are performed on the linearized system model. Numerical simulation results show that the control method designed in this paper possesses high attitude control accuracy and stability.