北京航空航天大学学报 ›› 2022, Vol. 48 ›› Issue (4): 665-673.doi: 10.13700/j.bh.1001-5965.2020.0617

• 论文 • 上一篇    下一篇

柔性翼气动力和变形特性的实验研究

王涵斌, 贺曦, 王晋军   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2020-11-04 发布日期:2022-04-27
  • 通讯作者: 王晋军 E-mail:jjwang@buaa.edu.cn
  • 基金资助:
    国家自然科学基金国际合作项目(11761131009);创新研究群体项目(11721202)

Experimental study on aerodynamic and deformation characteristics of flexible membrane wing

WANG Hanbin, HE Xi, WANG Jinjun   

  1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
  • Received:2020-11-04 Published:2022-04-27

摘要: 微型飞行器在军、民用领域具有广阔的应用前景,柔性翼是提升微型飞行器的气动性能的有效方法。为了更好地对柔性翼进行控制,对柔性翼变形和振动特性及其对气动力的影响进行了同步测量。研究结果表明,相比于刚性翼,柔性翼使失速迎角推迟了6°,最大升力系数提升了47.4%,升阻比提高了17.8%。柔性翼的周期性振动除了迎角0°~2°呈现大振幅、小静变形特征外,振动的振幅随着迎角增加经历无明显波峰、三波峰到单波峰的转换。升力系数最大时对应的薄膜变形、振动振幅均达到最大。此外,变形最大的弦向位置随迎角的变化决定了俯仰力矩的特性。据此提出了施加弯度和特定频率的振动激励来提升气动性能的主动控制策略。

关键词: 柔性翼, 流固耦合, 气动力测量, 变形测量, 振动分析

Abstract: Micro air vehicles (MAV) have wide appications in both miltary and civilian fields, and flexible membrane wings are an effective method to improve the aerodynamic of MAV. In order to better control the flexible wing, the vibration and deformation characteristics of the flexible membrane wing and their impact on aerodynamic force are measured synchronously. Compared with the rigid wing, for the flexible membrane wing, the stall angle of attack is delayed by 6°, the maximum lift coefficient is increased by 47.4%, and the lift-drag ratio is increased by 17.8%. In addition to the characteristics of large amplitude and small static deformation at α=0°~2°, the amplitude of the periodic vibration of the flexible membrane wing undergoes a transition from no obvious crest, three crests to one crest as the angle of attack increases. When the lift coefficient is maximum, the corresponding membrane deformation and vibration amplitude both reach their maxima. Besides, the chordwise position of the maximum deformation changes with the angle of attack, which determines the pitching moment characteristics. Based on these results, an active control method of improving aerodynamic performance by applying deformation and vibration excitation with specific frequency is proposed.

Key words: flexible membrane wing, fluid-structure coupling, aerodynamic force measurement, deformation measurement, vibration analysis

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发