/PI Output Feedback Control of Aero-Engine Under Nonstrict Properness Based on LMI

WANG Xi; TAN Dao-liang

Chinese

您当前的位置：

首页 >

文章列表页 >

/PI Output Feedback Control of Aero-Engine Under Nonstrict Properness Based on LMI

更新时间：2026-07-07

- /PI Output Feedback Control of Aero-Engine Under Nonstrict Properness Based on LMI
- Vol. 19, Issue 2, Pages: 254-258(2004)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院,北京,100083
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2004
- 稿件说明：
移动端阅览
王曦, 覃道亮. 航空发动机H∞PI输出反馈控制——非严格正则LMI方法[J]. 航空动力学报, 2004, 19(2): 254-258.

WANG Xi, TAN Dao-liang. /PI Output Feedback Control of Aero-Engine Under Nonstrict Properness Based on LMI[J]. 2004, 19(2): 254-258.
王曦, 覃道亮. 航空发动机H∞PI输出反馈控制——非严格正则LMI方法[J]. 航空动力学报, 2004, 19(2): 254-258. DOI：

WANG Xi, TAN Dao-liang. /PI Output Feedback Control of Aero-Engine Under Nonstrict Properness Based on LMI[J]. 2004, 19(2): 254-258. DOI：

摘要

基于传递函数矩阵H∞范数的等价原则思想

将非严格正则模型转化为严格正则模型。通过LMI求解方法

在考虑控制能量约束的条件下

对严格正则模型进行静态输出反馈PI控制器设计。提出了一种非严格正则模型静态输出反馈PI控制器求解的算法。以某型双转子涡喷发动机为被控对象

进行静态输出反馈PI控制器的LMI设计

并分区域在飞行包线进行了动静态性能和鲁棒性能仿真验证。

Abstract

According to the physical meaning of the H∞ norm

a nonstrict proper model is converted into some strict proper model under the equivalence condition of their H_∞ norms.A static output feedback PI controller for the resulting strict proper model is designed on the basis of LMI

and control constraints are taken into consideration in the design process of the controller.An algorithm for solving the static output feedback PI controller is presented.This method is applied to the design procedure of aero-engine controller.The dynamical and static performances of the aero-engine control system are verified at different partitioned regions of flight envelope.

关键词

Keywords

references

Views

467

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Application of Robust Control to the Design of Jet Engine Digital Controller

Optimization Methodology of PI Controller Parameters for Aeroengines Based on Genetic Algorithm

LMI Based Multivariable H_∞Fixed-Order Control for an Aero-Engine

Prediction method on equivalent thermal conductivity coefficient of plain braided C/SiC composites material based on finite element method

Aerodynamic characteristics of design Mach number of 5 two-dimensional inlet with mixed-compression under typical condition

Related Author

WANG Xi

YANG Jie

TAN Dao-liang

TIAN Xin-feng

WANG Hai-long

SU Wei-sheng

LI Yue

SUN Jian-guo

Related Institution

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

Beijing Changkong Machinery Company Ltd.

The College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

China Aviation Motor Control System Institute,AVICI

Northwestern Polytechnical University

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰