纵向控制律的LQR设计及性能检验

LQR Design and Performance Examination of Longitudinal Control Law

阐述了线性二次型状态反馈(LQR)理论在飞行控制系统设计中的优势。针对现代飞机飞行控制系统的特点,即典型的非线性、多回路和强耦合控制系统,介绍了纵向飞行控制系统的设计过程。选择俯仰速率、法向过载以及升降舵输出等信号作为输出变量,使传统LQR最优控制中对加权阵Q和R的选择变为对降维的加权阵Q的选择,并通过飞行速度进行动态调参。最后,以某型飞机为例设计了控制律,并进行数字仿真和性能分析,同时对所设计的控制器进行了脆弱性检验。

The paper describes the advantage of LQR theory to flight control system design of an airplane.On account of longitudinal flight control system of an airplane is a control system with the feature non-linear,multi-loop and tight coupling,the design method of the longitudinal flight control system is introduced in detail.Feedback signals and elevator input are selected as outputs,the paper changes selection of weight matrices Q and R of LQR optimal control to selection of reduced-order weight matrix Q,according to flight velocity to adjust feedback parameters.Design of the flight control laws based on an airplane,simulation and performance analysis,and the controller is examined with the fragility standard.