Numerical study of wing gust response alleviation based on camber morphing trailing edge

被引：0
|
作者：
Wei R. [1 ]
Dai Y. [1 ]
Yang C. [1 ]
Yu S. [1 ]
机构：
[1] School of Aeronautic Science and Engineering, Beihang University, Beijing
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2023年 / 49卷 / 07期
基金：
中国国家自然科学基金;
关键词：
active control; camber morphing trailing edge; gust response alleviation; reduced order model; unsteady aerodynamic force;
D O I：
10.13700/j.bh.1001-5965.2021.0563
中图分类号：
学科分类号：
摘要：
A mathematical model for gust response analysis is established for a wing with camber morphing trailing edges, and a simulation study of gust response alleviation is carried out. The computational fluid dynamics method is used to calculate the generalized unsteady aerodynamic force under the given dynamic morphing of the trailing edge, and the generalized aerodynamic force model under the dynamic deflection of the trailing edge is established based on the state observer method,. The panel method is used to calculate the generalized aerodynamic force caused by mode motion and gust, while the generalized predictive control (GPC) method is used in the design of gust alleviation control law. On this basis, the aerodynamic characteristics of the camber morphing trailing edge and the traditional hinged flap are compared. The simulation results show that the GPC method based on the camber morphing trailing edge can effectively alleviate the wing-tip acceleration response caused by gust, and the wing-tip acceleration reduction efficiency is 44.25%. The wing with morphing trailing edge has a more continuous pressure distribution on the upper and lower surfaces, a greater impact on the aerodynamics, and higher acceleration reduction efficiency. The use of camber morphing trailing edges for gust alleviation has a broader application prospect. © 2023 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
引用
收藏
页码：1864 / 1874
页数：10
相关论文
共 22 条
  • [1] RIVERO A E, FOURNIER S, MANOLESOS M, Et al., Experimental aerodynamic comparison of active camber morphing and trailing-edge flaps, AIAA Journal, 59, 7, pp. 2627-2640, (2021)
  • [2] ZHU L Q, SUN G K, LI H, Et al., Intelligent and flexible morphing wing technology: A review, Journal of Mechanical Engineering, 54, 14, pp. 28-42, (2018)
  • [3] HUNTLEY S J, WOODS B K, ALLEN C B., Computational analysis of the aerodynamics of camber morphing: AIAA 2019-2914, (2019)
  • [4] NGUYEN N T, CRAMER N B, HASHEMI K E, Et al., Progress on gust load alleviation wind tunnel experiment and aeroservoelastic model validation for a flexible wing with variable camber continuous trailing edge flap system: AIAA 2020-0214, (2020)
  • [5] TAL E A, NGUYEN N T., Unsteady aeroservoelastic modeling of flexible wing generic transport aircraft with variable camber continuous trailing edge flap: AIAA 2015-2722, (2015)
  • [6] NGUYEN N, TING E, LEBOFSKY S., Aeroelastic analysis of a flexible wing wind tunnel model with variable camber continuous trailing edge flap design, AIAA Science and Technology Forum and Exposition, (2015)
  • [7] TING E, CHAPARRO D, NGUYEN N, Et al., Optimization of variable-camber continuous trailing-edge flap configuration for drag reduction, Journal of Aircraft, 55, 6, pp. 2217-2239, (2018)
  • [8] HERRERA C Y, SPIVEY N D, LUNG S, Et al., Aeroelastic airworthiness assessment of the adaptive compliant trailing edge flaps, Proceedings of the 46th Society of Flight Test Engineers International Symposium, pp. 14-17, (2015)
  • [9] KOTA S, FLICK P, COLLIER F S., Flight testing of FlexFloil<sup>TM</sup> adaptive compliant trailing edge, 54th AIAA Aerospace Sciences Meeting, (2016)
  • [10] CHEN L, WU Z G, YANG C, Et al., Active control and wind tunnel test verification of multi-control surfaces wing for gust alleviation, Acta Aeronautica et Astronautica Sinica, 30, 12, pp. 2250-2256, (2009)
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