探讨飞行器翼身不同结构刚度对翼尖位移和结构重量的关系  

Discussion on the Relation Between Structural Weight and Wing Tip Displacement with Respect to Different Stiffness of Aircraft Wing and Fuselage

作　　者：邓扬晨[1] 陈华[2] 章怡宁[1] 

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035 [2]西北工业大学机电工程学院,陕西西安710072

出　　处：《航空计算技术》2007年第4期1-3,8,共4页Aeronautical Computing Technique

基　　金：航空科学基金(03B53003);辽宁省科学技术航空专项基金(20044007)

摘　　要：为了研究大展弦比双机身布局无人机中翼身结构不同刚度对结构响应的影响,本文采用有限元分析与满应力优化相结合来探讨这一问题。计算结果表明:机翼与机身之间不同刚度对结构响应存在影响。建议结构设计时注意这一现象并加以利用,从而得到轻量化的结构设计。针对算例进一步计算与分析表明:采用本文方法得到的结构优化方案,同样也能够满足该飞机的静、动气弹要求。结论:采用本文方法,不仅可以研究飞机部件之间不同刚度对飞机结构响应的影响,还可以进行全机的结构方案设计,并对此方案进行刚度、强度、颤振和控制面效率的分析与评估。In order to deal with the effect of structural response due to different stiffness on wing and fuselage structure with high aspect ratio, the author proposed an approach by combining a finite element method （FEM） and a full stress design （FSD） to solve this problem. Computational results showed that it was true to exist the effect above mentioned. The author suggested that aircraft structural designer should pay attention to it and utilized it so as to get light structural design. Moreover, with respect to the example, the proposed method could offer a conceptual structural design that satisfies static and dynamic aeroelastic requirements. Finally the conclusion was drawn for this paper.

关 键 词：大展弦比 结构 刚度 结构响应 优化 

分 类 号：V214[航空宇航科学与技术—航空宇航推进理论与工程]