大展弦比机翼剖面刚度分析  

Investigations of High Aspect Wing's Cross Section Rigidity

作　　者：侯甲栋[1] 冯蕴雯[1] 薛小锋[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《航空计算技术》2011年第1期34-37,43,共5页Aeronautical Computing Technique

基　　金：国家自然科学基金资助项目(10577015);航空科学基金资助项目(2008ZA53006);国防科工委民机预研课题资助项目

摘　　要：通过对变截面悬臂梁在一端受载时,自由端的位移、转角和悬臂梁各剖面刚度之间关系的分析,推导出一种基于有限元模型的剖面刚度计算方法。针对某型飞机,对机翼结构进行适当简化,建立机翼主承力结构的有限元模型,采用所推导出的方法计算了机翼沿展向各剖面的刚度,其结果可为某型飞机机翼结构设计和气动弹性分析提供参考。According to relationship between the displecement and deflection of the unrestrained tip and the rigidity of each cross section of a cantilever which is loaded on the unrestrained tip,a method to calculate cross section rigidity of a cantilever based on a finite element model has been deduced in this paper.To a certain aircraft,the wing structure has been predigested seemly,and the finite element model of the wing box has been constituted,then the cross section′s rigidity of the wing box has been calculated by using the method deduced from this paper.It shows that the result can be applied to the aeroelasticity design and analysis of the aircraft wing.

关 键 词：机翼 翼盒 有限元 弯曲刚度 扭转刚度 

分 类 号：O242.21[理学—计算数学]