Wind tunnel test on gust alleviation control strategies of elastic wing

被引：0

作者：

Zeng X. ^{[1
]}

Zhao D. ^{[1
]}

Li J. ^{[1
]}

Yan Z. ^{[1
]}

Liu C. ^{[1
]}

机构：

[1] Aircraft Strength Design and Research Department, AVIC The First Aircraft Institute, Xi’an

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 04期

关键词：

control strategy; gust alleviation; gust sensing; high-aspect-ratio wing; modal damping enhanced; wind tunnel test; wing root bending moment; wing tip acceleration;

D O I：

10.7527/S1000-6893.2022.26869

中图分类号：

学科分类号：

摘要：

Two control strategies for gust alleviation of elastic wing are introduced. The first control strategy is Modal Damping Enhanced Gust Alleviation（MDEGA）. The ailerons are driven to deflect in unloading direction by feedback of wing tip vibration velocity，so as to alleviate the dynamic load and vibration of the wing. The other control strategy is called Gust Sensing Based Gust Suppression（GSBGS）. The gust detector senses the gust velocity and feeds it for⁃ ward to actuate ailerons. Then the control force is generated on aileron to counteract the gust load. In order to verify the implemental effect of these two control strategies，a principle wind tunnel test is conducted with the high-aspect-ratio wing of an elastic aircraft scale model as the research object. The experimental results showed that the two con⁃ trollers both significantly reduced the gust response of the 1st wing bending mode and the peak reduction ratio in terms of wing root bending moment as well as wing tip acceleration exceeded 50%. Compared with MDEGA，GSBGS con⁃ troller is more effective on gust alleviation at frequencies other than the peak frequency. The two strategies have their own characteristics which can provide reference for engineering design：MDEGA is equivalent to increasing structural damping which is independent of gust measurement but constrained by aeroservoelastic stability；GBSGS is essen⁃ tially an open loop controller，which means its influence on aircraft dynamic behavior can be ignored，whereas it relies greatly on accurate gust detection. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.

引用

共 22 条

[21] ZHAO Z L，, CHEN T Y，, TANG C，, Et al., The gust load alleviation design and flight tests for an aircraft with large aspect ratio［J］, Aircraft Design, 38, 5, pp. 17-20, (2018)
[22] YANG Y, YANG C, WU Z G., A design of gust allevia⁃ tion control system based on test of actuator's dynamic characteristics［J］, Journal of Vibration and Shock, 39, 4, pp. 106-112, (2020)

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