Design and simulation of sliding mode regulator for turbo-fan engine parameter limit

张园锁; 吕晓武; 杨梅菊

doi:10.13224/j.cnki.jasp.2017.06.020

Chinese

您当前的位置：

首页 >

文章列表页 >

Design and simulation of sliding mode regulator for turbo-fan engine parameter limit

更新时间：2026-07-07

- Design and simulation of sliding mode regulator for turbo-fan engine parameter limit
- Vol. 32, Issue 6, Pages: 1425-1433(2017)
- 作者机构：
  
  中国航空发动机集团有限公司商用航空发动机有限责任公司,上海,201108
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2017.06.020
  CLC：
- Published：2017
- 稿件说明：
移动端阅览
张园锁, 吕晓武, 杨梅菊. 涡扇发动机滑模参数限制调节器设计与仿真[J]. 航空动力学报, 2017, 32(6): 1425-1433.

doi: 10.13224/j.cnki.jasp.2017.06.020
张园锁, 吕晓武, 杨梅菊. 涡扇发动机滑模参数限制调节器设计与仿真[J]. 航空动力学报, 2017, 32(6): 1425-1433. DOI： 10.13224/j.cnki.jasp.2017.06.020.

doi: 10.13224/j.cnki.jasp.2017.06.020 DOI：

摘要

以涡扇发动机参数限制保护为目标设计了一种滑模(SM)调节器.采用区域极点配置的混合范数综合法设计了滑模调节器的反馈增益系数；根据全局渐近稳定性判据验证了本滑模控制仿真的稳定性；基于滑模调节器在仿真环境中进行了控制系统的建模，对不同的滑模可调参数切换增益进行了比对分析，并选取了某一组切换增益值作为后续仿真的基准参数；仿真对比分析了滑模调节器和线性调节器的调节效果.结果表明：基于滑模控制方法所设计滑模参数限制调节器在发动机过渡态过程中对发动机进行主控，克服了线性参数限制调节器在过渡态过程几乎无法实施控制的缺点；该设计的滑模参数限制调节器能在7s内实现发动机过渡态的参数限制保护功能.

Abstract

A sliding mode (SM) regulator was proposed for the turbo fan engine parameter limit protection. The feedback gains of the SM were designed using the regional pole placement method based on the mixed norm synthesis. The overall asymptotic stability of the SM regulator was established. The SM regulator was verified and compared in the simulation with different sliding switch gains

of which one of the gains was used as the standard coefficient for the following simulations. The regulating effects between SM regulator and linear regulator were compared and analyzed. The results preliminarily show that

the parameter limit regulator acts as a main control regulator during engine transient state process based on sliding mode control theory

overcoming the drawback of linear parameter limit regulator which nearly can not work during the same process; the designed regulator can conduct the parameter limit protection function in 7 seconds during the engine transient state.

关键词

Keywords

references

Views

470

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Turbo-fan engine fault diagnosis based on adaptive particle filtering

Rapid prototype real-time simulation of turbo-fan engine sensor fault diagnosis

Concurrent structural and material optimization of turbine frame in turbo-fan engine

Rapid prototype design for turbo-fan engine fault diagnosis

Numerical caculation of flow and acoustics fields for separated exhaust nozzle with bypass offset

Related Author

LU Feng

FENG Min

HUANG Jin-quan

YIN Bin-bin

WANG Ji-qiang

YE Zhi-feng

ZHAO Cheng-wei

SONG Ying-dong

Related Institution

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

Innovation Center for Advanced Aero-Engine

Aviation Motor Control System Institute, Aviation Industry Corporation of China

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

Representative Office Stationed 420 Factory, Chinese People's Liberation Army

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