摘要
对具有不确定性的高超声速飞行器在输入受限情况下的稳定控制问题,基于线性矩阵不等式(LMI)技术提出了一种具有指数收敛速率的控制器设计方法。将飞行器模型中的不确定性视为总和扰动,针对存在不确定性的输入受限系统给出了一种具有指数收敛速度的不变集条件,并利用LMI技术将控制器的设计问题转化为受限系统吸引域的最优化问题。仿真结果表明,在气动参数摄动和控制量存在饱和的情况下,本文设计的指数收敛控制器具有良好的动态特性和鲁棒性。
Regarding stability control of a hypersonic vehicle in the presence of input saturation and uncer- tainties, a controller with exponential convergence rate is designed, which is based on LMI technique. The uncertainties of hypersonic vehicle model are regarded as ＂total disturbance＂, an exponential convergence condition for invariant set of systems subject to input saturation and disturbance is derived. By using LMI technique, controller design is transformed into maximization of the domain of attraction. The simulation results show good dynamic characteristics and robustness of the proposed method in the presence of aerody- namic dispersion and control input saturation.
作者
关英姿
朱凯
Guan Yingzi Zhu Kai(School of Astronautics, Harbin Institude of Technology, Harbin 150001 Beijing Institute of Aerospace Technology, Beijing 100074, China)
出处
《航天控制》
CSCD
北大核心
2017年第3期34-39,共6页
Aerospace Control
关键词
高超声速飞行器
输入受限
不确定性
线性矩阵不等式
指数收敛
Hypersonic vehicle
Input constraints
Uncertainties
Linear matrix inequalities （LMI）
Ex-ponential convergence
