大展弦比飞机翼身结构不同刚度对结构响应的影响  

Effects of Different Stiffness between Wing and Fuselage Structures on Structural Responses for High Aspect Ratio Airplanes

作　　者：邓扬晨[1] 孙颖[2] 曾惠华[1] 陈华[3] 

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035 [2]中国人民解放军驻沈阳飞机工业(集团)有限公司军事代表室,辽宁沈阳110034 [3]西北工业大学机电工程学院,陕西西安710072

出　　处：《飞机设计》2006年第4期1-6,共6页Aircraft Design

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

摘　　要：为了研究大展弦比双机身布局无人机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 effects of different stiffness between wing and fuselage structures on structural responses for high aspect ratio, twin-fuselage unmanned aerial vehicle（UAV） configurations, the authors proposed an approach to exploring the problem by combining finite element method（FEM） and full stress design （FSD）. Computational results showed that wing stiffness different from fuselage stiffness have effects on structural responses. This point should be considered in the design to lead to a light-weight structure design. The further computation and analysis indicated that structure optimization concepts obtained using this approach can achieve static and dynamic aero-elasticity requirements. Fi- nally, it was concluded that this approach may be used for the study of effects of different stiffness be- tween airframe components on structural responses, as weU as the analysis and evaluation of stiffness,strength, flutter, and control surface efficiency in the conceptual design of airframe structures.

关 键 词：大展弦比 结构 刚度 结构响应 优化 

分 类 号：V221.5[航空宇航科学与技术—飞行器设计]