Boundary protection control method of helicopter power system based on flight test analysis

被引:0
作者
Song Z. [1 ]
Zhao J. [1 ]
Yang W. [1 ]
机构
[1] Chinese Flight Test Establishment, Xi’an
来源
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2023年 / 49卷 / 01期
关键词
flight safety; flight test analysis; helicopters; power system; speed of power turbine; total distance control law; turboshaft engine;
D O I
10.13700/j.bh.1001-5965.2021.0431
中图分类号
学科分类号
摘要
Turboshaft engine is the main part of the power system of rotor aircraft such as helicopter. Once the key engine parameters exceed the limit, the method of reducing fuel quantity and power is generally adopted to limit, which will temporarily reduce the speed of power turbine, making it about 4%−6% lower than the normal rated state. However, if the overlimit state is not removed in time, the speed of the power turbine will continue to decrease, threatening the flight safety. Based on the flight test analysis of a certain helicopter from phenomena to data to solve the above problems. This paper proposes a control method, through the design from the total distance control law, achieve dynamic system boundary protection control in the condition of engine parameters overrun. if overrun status can’t get out timely, then engine change automatically to recover the normal control of power system. This method significantly enhances the robustness of helicopter power system control and the safety of the flight. The correctness of the design is verified by modeling the power system and simulating the control law. © 2023 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
引用
收藏
页码:100 / 105
页数:5
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