基于特征函数法的大展弦比机翼静气动弹性系统的数值计算与分析  

Calculation and Analysis of Static Aeroelastic Systems with a High-aspect-ratio Wing Based on the Characteristic Function

作　　者：王云海 李晨曦[1] 唐文勇 张宪明[2] 马瑞群[3] 孙永贺 WANG Yun-hai;LI Chen-xi;TANG Wen-yong;ZHANG Xian-ming;MA Rui-qun;SUN Yong-he(School of Aeronautics and Astronautics,Shandong Jiaotong University,Jinan 250357,China;School of Mechanical Engineering,Guizhou Institute of Technology,Guiyang 550003,China;Institute of Vibration Engineering Research,State Key Lab of Mechanics and Control for Mechanical Structures,Nanjing 210016,China)

机构地区：[1]山东交通学院航空学院,山东济南250357 [2]贵州理工学院信息工程学院,贵州贵阳550003 [3]南京航空航天大学机械结构力学及控制国家重点实验室,江苏南京210016

出　　处：《数学的实践与认识》2023年第1期152-162,共11页Mathematics in Practice and Theory

基　　金：山东省博士科研启动基金(BS2020022);校基金项目(Z202016);贵州省科技厅项目(黔科合基础[2017]1408号)。

摘　　要：飞行器结构在空气动力作用下会发生弹性变形,这种弹性变形反过来又使空气动力随之改变,由此形成气动弹性现象.一般来说,大展弦比机翼气动弹性分析需同时考虑扭转变形、弯曲变形及其相互耦合的效应.重点放在前者,即研究大展弦比机翼静气动弹性扭转发散问题,具有模型简单、更适合于机理分析.借助于特征值理论,针对“杆-梁”机翼模型分析机翼展向攻角的变化规律,探察数值模态解与理论解之间的差异.算例试验表明,特征值问题的理论发散解与事实不符,不能应用于工程实践.建议从展向攻角分布规律中寻找发散速度解.此外,计算后的攻角分布可为载荷重新分布等后续问题研究提供参考。Under the action of aerodynamic forces,one aircraft structure elastic deformation often occurs.In turn,structural deformation results in the change of the aerodynamic forces.We call this kind of interaction aeroelastic phenomena.In general,We have to taking into account the torsional deflection,bending deformation and its effect of mutual coupling as one aeroelastic analysis of high-aspect-ratio wing.This paper focuses on the former,namely study of static aeroelasticity of large aspect ratio wing on the divergence problem because it's a simple model and more suitable for mechanism analyses.Base on Eigenvalue theory,the rod-beam wing mode is investigated to find out varying pattern of span-wise angle of attack in comparison of the analytical solution and the numerical solution.Numerical Experiments show that the result applying the Eigenvalue theory is unbelievable contrary to the true situation.We sugyest seeking the lowest futter velocity base on the distribution of angles of attack.In addition,the results of the distribution of angles of attack can be helpful to the analysis of load redistribution.

关 键 词：大展弦比机翼 片条气动力 特征值问题 模态正交基 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]