摘要
研究仅采用磁力矩器作为执行机构的近地小卫星姿态控制问题。通过对刚体卫星的非线性动力学和运动学方程在平衡点处进行线性化处理,得到一个线性周期时变系统,应用线性二次最优调节器理论设计出最优磁矩控制律。最后针对某小卫星进行了仿真验证,结果表明所设计的最优控制律可以很好地完成三轴姿态稳定任务。
The attitude control problem of low earth orbit （LEO） satellites actuated by magnetorquers only is investigated. By linearizing the nonlinear dynamic and kinematic equations of rigid satellites, a linear periodically time-varing system is obtained. The linear quadratic optimal regulator theory is applied to design an optimal control law for magnetorquers. Simulation results show that the designed optimal magnetic control law can stabilize three-axis attitude of satellites effectively.
出处
《空间控制技术与应用》
2008年第5期61-64,共4页
Aerospace Control and Application
关键词
小卫星
姿态控制
LQR
磁控制
small satellite
attitude quadratic regulator （LQR）
magnetic control
linear control
