Aero-engine fault-tolerant control based on mode switch

YANG Zheng-shan; QIU Xiao-jie; ZHUANG Xi-ming; HUANG Jin-quan

doi:10.13224/j.cnki.jasp.2014.04.028

Chinese

您当前的位置：

首页 >

文章列表页 >

Aero-engine fault-tolerant control based on mode switch

更新时间：2026-07-07

- Aero-engine fault-tolerant control based on mode switch
- Vol. 29, Issue 4, Pages: 953-964(2014)
- 作者机构：
  
  1. 中国航空工业集团公司航空动力控制系统研究所,江苏,无锡,214063
  2. 南京航空航天大学能源与动力学院,南京,210016
  3. 总参陆航部驻上海地区军事代表室,上海,200233
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.04.028
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
杨征山, 仇小杰, 庄锡明, 黄金泉. 基于模态切换的航空发动机容错控制[J]. 航空动力学报, 2014, 29(4): 953-964.

doi: 10.13224/j.cnki.jasp.2014.04.028
杨征山, 仇小杰, 庄锡明, 黄金泉. 基于模态切换的航空发动机容错控制[J]. 航空动力学报, 2014, 29(4): 953-964. DOI： 10.13224/j.cnki.jasp.2014.04.028.

doi: 10.13224/j.cnki.jasp.2014.04.028 DOI：

摘要

综合了航空发动机控制和故障诊断方法

设计了基于模态切换的任务级和发动机级模式的容错控制系统.任务级模式在发动机部件故障时

通过切换控制策略和控制模式达到恢复或降低发动机性能的要求;发动机级模式在控制回路失效时

根据故障情况切换到容错控制回路

从而保证发动机继续正常工作.数字仿真结果表明:在稳态或加速过程中出现部件故障时

容错控制系统都能够100%恢复发动机的推力;在发动机中间、慢车和节流状态下

当压气机转速控制回路失效时

容错控制系统能够在3s内平稳切换到风扇转速控制回路.

Abstract

By combining aero-engine control and fault diagnoses methods

the aero-engine fault-tolerant control system based on control mode switch was designed

including task-level mode and engine-level mode. In case of failure of the engine components

the task-level mode could change the control strategies and modes to recover or reduce the aero-engine performance. In case of failure of a control loop

the control strategies were switched to other fault-tolerant control loops according to fault conditions

so as to ensure that the aero-engine continues to work normally. Numerical simulation result shows

the designed fault-tolerant control system can recover the aero-engine performance in 100% in case of failure of the components in the process of steady state or accelerated. And the designed fault-tolerant control system can switch to the fan speed control loop smoothly in 3 seconds in case of failure of the compressor speed control loop.

关键词

Keywords

references

Views

817

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Optimal guaranteed cost fault-tolerant control with bi-index constraints for aero-engine distributed control system

Development path and future trend of carrier-based advanced trainer engine

Thermal protection effectiveness of thermal barrier coatings in turbine blade applications

Aero-engine cycle design approach for multiple operating conditions performance reliability

Relationship between rotor/vanes blade number andnodal diameter number of bladed-disk coupling vibration

Related Author

WANG Lei

XIE Shou-sheng

PENG Jing-bo

YANG Yong

REN Li-tong

PENG Yunlong

WU Xiong

DING Ting

Related Institution

Aeronautics and Astronautics Engineering College, Air Force Engineering University

Unit 93704 of the Chinese People's Liberation Army

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

北京航空航天大学能源与动力工程学院

中国航天科技集团有限公司中国空间技术研究院北京卫星制造厂

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