三轴稳定小卫星LQG姿态稳定控制与仿真  

LQG Controller and Simulation for Three-axis Stabilized Small Satellite

作　　者：魏静波[1] 刘昆[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《系统仿真学报》2011年第8期1739-1742,共4页Journal of System Simulation

摘　　要：建立了三轴稳定小卫星稳定工作模式下的动力学模型,在此基础上设计了用于其姿态稳定控制的线性二次高斯型(LQG)控制器。该控制器由Kalman滤波状态估计器和线性二次型最优调节器两部分组成,前者对卫星姿态信息进行滤波融合,在此基础上,后者进行反馈增益矩阵的最优化设计。由三轴正交反作用飞轮系统提供控制力矩,得到了卫星姿态稳定系统的状态空间仿真模型。仿真结果表明:设计的LQG控制器可以实现卫星姿态的精确确定和稳定控制,姿态确定精度相对于敏感器测量精度有较大提高;二次型调节器能够对卫星姿态小偏置量进行快速稳定,而且可以较好地抑制卫星稳定工作时受到的外界干扰。The attitude dynamic model was established for the attitude steady working mode of a three-axis stabilized small satellite.Based on this model,a LQG（Linear-quadrics-Gauss） controller was employed,which is composed of a Kalman filter and a LQ modulator performing as the states estimator and an optimal controller respectively.The estimated attitude states were generated by Kalman filter based on the measurement from sensors,and the feedback-gain matrix was obtained by the modulator,utilizing the estimated states.The control torque was generated by three flywheels and the whole simulation model was also obtained.The numerical simulation results indicate that the LQG proposed could achieve the high level accurate attitude determination and fast steady control for this attitude control system,and perform well under the disturbance.

关 键 词：LQG控制器 姿态控制 KALMAN滤波 姿态确定 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]