柔性机翼阵风响应与被动减缓研究  

Research on Gust Response and Passive Alleviation of Flexible Wing

作　　者：刘湘一[1] 阎永举 文柏衡 王允良[1] LIU Xiangyi YAN Yongju WEN Baiheng WANG Yunliang(Department of Airborne Vehicle Engineering, NAAU, Yantai Shandong 264001, China The 91467^th Unit of PLA, Qingdao Shandong 266311, China Military Representatives Office of Navy in Zhuzhou, Zhuzhou Hunan 412000, China)

机构地区：[1]海军航空工程学院飞行器工程系 [2]91467部队 [3]海军驻株洲地区军事代表室

出　　处：《海军航空工程学院学报》2016年第6期635-640,共6页Journal of Naval Aeronautical and Astronautical University

基　　金：中国航空科学基金资助项目(20145784010)

摘　　要：高空长航时无人机的机翼展弦比大、柔性较强,飞行过程中极易受到阵风的影响。文章以几何精确本征理论建立结构模型,耦合Pitt-Peters动力入流理论建立柔性机翼非线性气弹模型,研究了柔性机翼阵风响应以及翼尖被动阵风减缓效应。采用空间-时间平行的有限元离散方法,将气弹方程转化为一阶微分代数方程,NewtonRaphson和Generalized-α算法分别用于静态变形和动态响应的求解,通过算例研究了离散阵风载荷下柔性机翼的阵风响应,结果表明翼尖被动阵风减缓装置对机翼变形有明显的减缓效果。One significant feature of high altitude long endurance UAVs is having with high-aspect-ratio flexible wings,which are extremely susceptible to excessive gust loads in this paper, an investigation was presented into minimizing the gust response of flexible wing integrated with a passive gust alleviation device（PGAD） at the wing tip. Based on geometrically exact, fully intrinsic theory and Pitt-Peters dynamic inflow theory, the governing aeroelastic model was developed as first-order algebra differential equations by space-time finite discretization. The Newton-Raphson method and Generalized-α method were used for static equilibrium and time simulation. Finally, the gust response of certain flexible wing to a discrete（1-cosin） gust load was studied. The results showed that the PGAD was effective on gust response reduction in term of deflection.

关 键 词：柔性机翼 气动弹性 阵风响应 被动减缓 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]