Control law of turboshaft engine for helicopter autorotation training

HUANG Kai-ming; HUANG Jing-quan; ZHOU Wen-xiang; FENG Xing; HUANG Bo

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Control law of turboshaft engine for helicopter autorotation training

更新时间：2026-07-07

- Control law of turboshaft engine for helicopter autorotation training
- Vol. 24, Issue 11, (2009)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院,南京,210016
  2. 中国航空工业集团公司中国航空动力机械研究所,株洲,412002
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
移动端阅览
HUANG Kai-ming, HUANG Jing-quan, ZHOU Wen-xiang, et al. Control law of turboshaft engine for helicopter autorotation training[J]. 2009, 24(11).
DOI：

HUANG Kai-ming, HUANG Jing-quan, ZHOU Wen-xiang, et al. Control law of turboshaft engine for helicopter autorotation training[J]. 2009, 24(11). DOI：

摘要

为确定直升机自转下滑训练过程发动机的控制规律

分析了采用正常控制规律进入自转状态时涡轴发动机的变化过程

提出了在现有控制规律基础上增强动力涡轮转速控制模块中总矩"提前器"作用和适当放宽速率限制值的控制对策.仿真结果表明

改进后的控制规律能够基本满足直升机对发动机状态控制的要求

为解决直升机发动机在自转训练情况下的控制问题提供了一条有效的技术途径.

Abstract

In order to deduce the engine control law during the helicopter autorotation

simulation was made to demonstrate the transient process of the engine when entering the helicopter autorotation condition using normal control law.Based on the existing control law

an improved law was brought forward by magnifying the differential gain of collective pitch "anticipator" and broadening the deceleration limitation.The simulation results show that the improved control law can satisfy the requirement of the helicopter

thus attaining an effective way for the control of the engine during the helicopter autorotation.

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Related Institution

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Unit ，People's Liberation Army

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西北工业大学动力与能源学院

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