不同后掠角大展弦比复合材料机翼气动特性  

Aerodynamic Characteristics Analysis of Different Sweepback Angles for High Aspect Ratio CompositeWings

作　　者：刘文一[1] 杨培源[1] 李厚旭 LIU Wenyi;YANG Peiyuan;LI Houxu(The 91550th Unit of PLA,Dalian Liaoning 116032,China)

机构地区：[1]91550部队,辽宁大连116023

出　　处：《海军航空大学学报》2023年第5期419-426,共8页Journal of Naval Aviation University

摘　　要：为了研究不同后掠角复合材料机翼的气动特性,建立了载荷模型;采用K方法通过Theodorsen函数推导得到了机翼颤振速度的计算公式,分析了0°、5°、10°、15°、20°、25°和30°共7种不同后掠角机翼的模态,得到了模态频率和模态振型;仿真计算得到了机翼的颤振速度和发生颤振时翼尖的最大垂直位移。结果显示:机翼后掠角为15°时,其颤振速度和翼尖最大垂直位移均在安全范围内,因此,后掠角15°,展弦比为26的机翼为飞行器机翼设计最优值。A model of loads is established to research aerodynamic characteristics of different sweepback angles for com-posite wings.The formula of flutter velocity formula derived by K-method using Theodorsen function.The modals of 7 different sweepback angles of 0°,5°,10°,15°,20°,25°and 30°are analyzed,the modal frequencies and modal shapes are found,flutter velocities and the maximum vertical displacement of wings when flutter occurs are obtained.It proves that the flutter velocity and the maximum vertical displacement are all in safe range,so the sweepback angle of 15°and the as-pect ratio of 26 is the optimal value for the aircraft wing design.

关 键 词：机翼 后掠角 颤振 模态 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]