蜻蜓滑翔时前翅褶皱的流固耦合分析  

Fluid-structure Interaction Simulation of Dragonfly's Forewing in Gliding Flight

作　　者：刘惠祥 何国毅[1] 罗云 LIU Hui-xiang;HE Guo-yi;LUO Yun(School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063

出　　处：《科学技术与工程》2018年第8期144-150,共7页Science Technology and Engineering

基　　金：国家自然科学基金(11462015)资助

摘　　要：滑翔是蜻蜓常见的一种飞行模式,为探究蜻蜓滑翔时气动力对前翅的影响,选取蜻蜓前翅横截面的褶皱,建立适当简化的二维数值模型——褶皱翼型,对二维褶皱翼型进行了单向和双向流固耦合分析。结果表明:褶皱的变形和应力随着攻角的增大而逐渐增大,且在同一攻角下,越靠近蜻蜓身体部分的横截面褶皱,变形和应力越大,越靠近前翅展向的外沿,变形和应力越小,褶皱的存在使蜻蜓前翅在受载荷后力学分布更加合理。Gliding flight is a common mode of dragonfly,the objective of the current research is to explore the effect of aerodynamics on the forewing of dragonfly during gliding flight,the folds of dragonfly s forewing cross section are selected to establish a simplified two-dimensional numerical model-pleated airfoil.The corrugated airfoils are acquired by using the unidirectional fluid-structure interaction calculation method and bidirectional fluid-structure interaction calculation method.Numerical simulation indicate that deformation and stress of the folds increase gradually with the increase of the angle of attack,the cross section of the dragonfly s body part is larger than the corrugation of wing s edge at the same angle of attack.It should be noted that using the unidirectional fluid-structure interaction calculation method at small angle of attack and using the unidirectional fluid-structure interaction calculation method at relatively large angle of attack,the distribution of stress of dragonfly s forewing is more reasonable owing to the corrugation s contribution.

关 键 词：滑翔 蜻蜓前翅 流固耦合 变形 应力 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]