基于等效刚度的大展弦比机翼结构分析方法  

Structural Analysis Method Based on Equivalent Stiffness Model for Large Aspect Ratio Wing

作　　者：刘东伟 王宇[1] LIU Dong-wei;WANG Yu(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016, China)

机构地区：[1]南京航空航天大学航空宇航学院,江苏南京210016

出　　处：《航空计算技术》2018年第6期68-72,76,共6页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(11602103);江苏省高校优势学科建设工程项目资助

摘　　要：通过等效刚度方法计算大展弦比机翼加筋壁板的刚度矩阵,建立与加筋板平面形状相同的等效板,并使等效板具有与加筋壁板相同的力学性能,从而简化大展弦比机翼有限元模型,达到缩短建模、分析、后期优化流程所需时间的目的。选取两个不同展弦比的机翼,分别建立绘制了桁条的详细有限元模型和等效刚度有限元模型。对两个模型静力学、动力学和颤振计算结果进行对比,数据表明两个模型的静力变形、固有频率、振动模态和颤振分析结果吻合度高,从而证明了等效刚度方法在大展弦比机翼结构有限元建模应用中的可行性。In order to simplify the finite element model of the large aspect ratio wing,and shorten the time needed formodeling,analysis,and later optimizationprocess,the equivalent stiffness method is used to calculate the stiffness matrix of wing stiffened panels with large aspect ratio.An equivalent plate with the same plane shape of stiffened plate is established.Application of the equivalent stiffness method makes the equivalent platehas the same mechanical properties as the stiffened panel.A detailed finite element model withactual structureand a finite element model of equivalent stiffness for large aspect ratio wing with different aspect ratio are established.The results of statics,dynamics and flutter for two models are compared,the data show that the static deformation,natural frequencies,vibration modes and flutter analysis results of the two models highly coincide with each other,as a result,it is proved that the equivalent stiffness method is feasible in the application of finite element modeling for the large aspect ratio wing structure.

关 键 词：机翼 大展弦比 复合材料 等效刚度 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程]