基于LMI的空间站角动量管理控制器多级设计  

Multistage Design of Angular Momentum Management Controller of Space Station Based on LMI

作　　者：王梦菲 张军[1,2] 李金哲[1] Wang Mengfei;Zhang Jun;Li Jinzhe(Beijing Institute of Control Engineering,Beijing 100190,China;National Laboratory of Space Intelligent Control,Beijing 100190,China)

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术国家级重点实验室,北京100190

出　　处：《航天控制》2020年第1期36-43,共8页Aerospace Control

基　　金：国家自然科学基金(68745511)。

摘　　要：针对空间站在轨飞行中引力梯度力矩和气动力矩常值部分带来的控制力矩陀螺角动量积累问题,建立了线性化动力学模型,并引入滤波变量将系统扩维以抑制常值以及一倍、二倍于轨道频率的干扰对姿态的影响;同时为避免传统线性二次型算法中加权矩阵选择困难和解决高维系统一次性求取反馈增益阵时遇到的数值奇异问题,将基于符号矩阵的系统解耦与线性矩阵不等式多目标约束算法结合,进行控制器的多级设计,使闭环极点配置到指定梯形区域内以满足动态和稳态性能要求,且使得不确定系统具有一定的鲁棒性。仿真结果表明了控制器的有效性。For the accumulation of control momentum gyro angular momentum during orbit operation caused by constant component of gravity gradient torque and aerodynamic torque,a dynamics model of space station is established.The state space equation is augmented by the filter states which are introduced to suppress the disturbance’s impact on attitude.In order to solve the problem of choosing weighted matrix in linear quadratic algorithm and avoid the problem of numerical singularity in high dimensional systems,firstly,the symbolic matrix is used to decompose the system for multistage controller design,and then the state feedback gain matrix is solved by linear matrix inequality and the closed-loop poles are placed to the trapezoidal region.Moreover,the controller is robust to system uncertainties.Finally,the simulation results demonstrate the effectiveness of the controller.

关 键 词：空间站 角动量管理 符号矩阵 线性矩阵不等式 极点配置 鲁棒稳定 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]