涡喷发动机H_∞控制参数化Ricati方程的解

推进技术 ›› 1999, Vol. 20 ›› Issue (3): 73-77.

涡喷发动机H_∞控制参数化Ricati方程的解

王曦,谢振华,曾庆福

北京航空航天大学工程系统工程系;海军航空技术学院航空军械系;西北工业大学航空动力与热力工程系

发布日期:2021-08-15
基金资助:
航空科学基金

SOLUTION OF PARAMETRIC RICCATI EQUATION ON TURBOJET ENGINE H ∞ CONTROL

Dept.of Aeroengine Engineering,Northwestern Polytechnical;Dept.of Aeroengine Engineering,Northwestern Polytechnical;Dept.of Aeroengine Engineering,Northwestern Polytechnical

Published:2021-08-15

摘要/Abstract

摘要： 由分块矩阵的奇异值不等式关系，给出了初猜值γ０、λ０的对半求解法，在此基础上直接给出带参数的Ｒｉｃｃａｔｉ方程迭代求解法。用此方法对涡喷发动机不确定性系统设计了控制器，并在发动机气动热力学非线性模型上进行了仿真验证，结果表明控制系统能够取得满意的鲁棒性能、抗干扰性能和伺服跟踪性能。

关键词: 涡轮喷气发动机;结构参数;鲁棒控制;仿真试验;性能分析

Abstract: Focused on solving parametric Riccati equation which is the key point of designing an output feedback robust H ∞ controller to structured parameter uncertain systems,the dichotomy for solving initial guess value γ 0,λ 0 was achieved using the relation of singular value inequality of blocked matrix.Furthermore,the iterative algorithm for parametric Riccati equations was presented directly.The controller to turbjiet engine with structured parameter uncertainty was designed and verified using simulations on nonlinear model of twin spool turbojet engine aerothermodynamics.It showed that robust disturbance rejection and servo tracking performance for control systems can be guaranteed.

Key words: Turbojet engine;Structured parameter;Robost control;Simulated test;Performance analysis

王曦,谢振华,曾庆福. 涡喷发动机H_∞控制参数化Ricati方程的解[J]. 推进技术, 1999, 20(3): 73-77.