一种直升机自旋训练过程涡轴发动机控制规律设计与仿真

严长凯; 周骁; 张海波

doi:10.13224/j.cnki.jasp.2014.07.030

一种直升机自旋训练过程涡轴发动机控制规律设计与仿真

doi: 10.13224/j.cnki.jasp.2014.07.030

南京航空航天大学能源与动力学院, 南京 210016

基金项目:

航空科学基金（20120652）

详细信息

作者简介:
严长凯（1989-），男，甘肃永昌人，硕士生，主要研究方向为航空发动机建模与控制。

中图分类号: V233.7
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- 被引次数: 0
出版历程
- 收稿日期: 2013-04-15
- 刊出日期: 2014-07-28

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

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 针对直升机自旋训练过程中涡轴发动机快速响应要求，提出了一种以燃油流量和导叶角为控制量的鲁棒控制规律抑制自由涡轮转速瞬态下垂.首先，通过改进UH-60直升机/T700发动机综合模型，使之能够模拟自旋进入及自旋恢复过程动态变化.其次，提出并设计一种基于燃油流量和导叶调节的涡轴发动机鲁棒控制规律，并通过典型的自旋训练过程仿真，验证了该控制规律相比仅以燃油流量为变量的控制规律，自由涡轮转速瞬态下垂量降低至3%以下，且燃油流量变化更加平缓，改善了执行机构的工作条件.
- 涡轴发动机 /
- 直升机 /
- 自旋训练 /
- 燃油流量 /
- 导叶角 /
- 鲁棒控制
Abstract: According to the special need of turbo-shaft engines for fast response in helicopter autorotaion training process, a robust control scheme for turbo-shaft engines, including both fuel mass flow and guided vanes angle control, was proposed and designed to reduce the turbine speed transient droop. Firstly, an improved comprehensive model of UH-60 helicopter/T700 engines, which can simulate autorotation decent and autorotation recovery, was presented. Secondly, robust control scheme for turbo-shaft engine based on fuel mass flow and guided vanes adjustment was preset in the simulation cases. The result shows clearly that the turbine speed transient droop, controlled by the proposed robust control scheme, is sharply reduced to 3% than traditional method only exploring fuel mass flow control, while the variation of fuel mass flow is much slower and the operation condition of the actuator is improved.
- turbo-shaft engine /
- helicopter /
- autorotation training /
- fuel mass flow /
- guided vanes angle /
- robust control

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参考文献(18)

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