Turbo-Fan Engine Dynamic Output Feedback Control with Mixed Weighted Sensitivity Based on LMI

TAN Dao-liang; WANG Xi; ZHEN Tie-jun

Chinese

您当前的位置：

首页 >

文章列表页 >

Turbo-Fan Engine Dynamic Output Feedback Control with Mixed Weighted Sensitivity Based on LMI

更新时间：2026-07-07

- Turbo-Fan Engine Dynamic Output Feedback Control with Mixed Weighted Sensitivity Based on LMI
- Vol. 20, Issue 2, (2005)
- 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：2005
- 稿件说明：
移动端阅览
TAN Dao-liang, WANG Xi, ZHEN Tie-jun. Turbo-Fan Engine Dynamic Output Feedback Control with Mixed Weighted Sensitivity Based on LMI[J]. 2005, 20(2).
DOI：

TAN Dao-liang, WANG Xi, ZHEN Tie-jun. Turbo-Fan Engine Dynamic Output Feedback Control with Mixed Weighted Sensitivity Based on LMI[J]. 2005, 20(2). DOI：

摘要

利用回路整形和内模原理方法

选取合理频率域加权函数

结合实际被控对象状态空间模型

得到某广义被控对象状态空间模型

将原控制要求问题转化为标准H∞控制问题。基于LMI(LinearMatrixInequality)方法

对此广义对象进行最优H∞动态输出反馈控制器设计

进而求得原被控对象的控制器。以某型涡扇发动机为被控对象

进行混合加权灵敏度H∞动态输出反馈控制器设计

并在飞行包线范围内

进行了发动机控制系统非线性仿真验证。结果表明

此控制器满足抗干扰性、跟踪性要求

并具有一定鲁棒性。

Abstract

Choosing appropriate weighted functions in the frequency domain

and in combination with the state-space model of the real plant

the formulation of the state-space model for some generalized plant by employing the method of loop shaping and internal principle was established.The original control problem was converted to a standard H_∞ problem.The controller for the original plant was derived by means of solving optimal H_∞ dynamic output feedback controller for the generalized plant based on Linear Matrix Inequality (LMI).This design procedure was applied to a turbo-fan engine.The controller obtained by this method was verified in a wide engine operating range in the flight envelope.Simulation results of the turbofan engine nonlinear model show that the characteristics of the controller

namely

tracking characteristics

disturbance rejection and robustness

are satisfactory.

关键词

Keywords

references

Views

448

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

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

Computation of effect of different nozzle parameters on internal performance of convergent-divergent axisymmetric nozzle

Study of novel flow control concept for fix-geometry two-dimensional mix-compression supersonic inlet

Nonlinear dynamic response analysis of unbalance-rubbing coupling faults of rotor-ball bearing-stator coupling system

Related Author

LU Si-da

GAO Xi-guang

SONG Ying-dong

WENG Xiao-chai

GUO Rong-wei

ZHU Dan-dan

SHAO Wan-ren

WENG Xiao-chai

Related Institution

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

Department of Power and Propulsion, School of Engineering, Cranfield University, Bedfordshire MK4

State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics

Unit 94710, the Chinese People's Liberation Army

Innovation Center for Advanced Aero-Engine

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