A new rapid response emergency control method for turbo-shaft engines

CHEN Guo-qian; ZHANG Hai-bo; YAN Chang-kai; WANG Jian-kang

Chinese

您当前的位置：

首页 >

文章列表页 >

A new rapid response emergency control method for turbo-shaft engines

更新时间：2026-07-07

- A new rapid response emergency control method for turbo-shaft engines
- Vol. 27, Issue 11, (2012)
- 作者机构：
  
  南京航空航天大学, 能源与动力学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2012
- 稿件说明：
移动端阅览
CHEN Guo-qian, ZHANG Hai-bo, YAN Chang-kai, et al. A new rapid response emergency control method for turbo-shaft engines[J]. 2012, 27(11).
DOI：

CHEN Guo-qian, ZHANG Hai-bo, YAN Chang-kai, et al. A new rapid response emergency control method for turbo-shaft engines[J]. 2012, 27(11). DOI：

摘要

针对直升机应急状态下特殊快速响应需求

基于涡轮放气原理

提出了一种新的应急状态快速响应控制方法.在应急状态下

除了燃油控制外

同时将涡轮放气量作为发动机控制变量

采用多变量鲁棒方法设计了应急状态直升机/涡轴发动机三变量快速响应控制器

该综合控制方法不仅实现了直升机垂飞通道的控制

而且在保持输出功率通道稳定

即自由涡轮转速恒定的前提下

借助于涡轮放气实现了燃气涡轮转速的闭环控制

有效实现了发动机功率快速跟随能力.最后

以直升机UH-60/涡轴发动机T700综合模型为对象

仿真验证了在直升机应急状态急升-急降过程中

直升机垂飞速度、发动机自由涡轮转速以及燃气涡轮转速跟踪指令的情况

结果表明:相比传统的PID(proportional integration differential)控制

基于快速响应控制方法建立的闭环系统响应迅速

动静态品质良好

能够达到直升机应急状态的特殊设计要求.

Abstract

According to the special need in helicopter's emergency state

a new fast response control method of integrated Helicopter/turbo-shaft engine system was proposed to solve this control problem for helicopter's emergency control.Turbine bleeding was another control input except for fuel flow in this new scheme

and the control law including three control loops was based on multi-variables robust control design theory.Specially in this hybrid control law

not only the helicopter climbing velocity was controlled

the gas turbine speed of turbo-shaft engines was also effectively controlled by turbine bleeding to realize engines' power rapid tracking while keeping the power turbine speed constant.In the final stage

the control law was implemented in an integrated UH-60 helicopter and T700 engine system and the transient performance of the closed-loop system in helicopter's climbing and desending emergency flights.The simulation results show clearly that the response time of the closed-loop system designed by the new fast response control law is much reduced compared with that designed by traditional PID(proportional integration differential) method

and it meets the special need of helicopter's emergency control.

关键词

Keywords

references

Views

488

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Design and simulation of a control scheme for turbo-shaft engine in helicopter autorotation training process

Design and application of a disturbance rejection rotor speed control method for turbo-shaft engines

Rotor speed changeable cascaded optimization method for helicopter/engine system

Optimal control of thrust for turboprop with engine and propeller integration during takeoff

Method on helicopter BVI noise reduction based onmiss-distance control

Related Author

YAN Chang-kai

ZHOU Xiao

ZHANG Hai-bo

SUN Jian-guo

SUN Li-guo

ZHANG Hai-bo

YAO Wen-rong

WANG Ri-xian

Related Institution

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

China Aviation Motor Control System Institute, Aviation Industry Corporation of China

Aero Engine Control System Institute， Aero Engine Corporation of China

National Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics

China Helicopter Research and Development Institute, Aviation Industry Corporation of China, Limited

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