文档介绍：南京航空航天大学
硕士学位论文
联结翼复合材料机翼结构优化设计与重量特性分析
姓名:乔巍
申请学位级别:硕士
专业:飞行器设计
指导教师:姚卫星
20090101
南京航空航天大学硕士学位论文
摘要
联结翼布局飞机可以被定义为由上反角的后掠前翼和下反角的前掠后翼联结在一起形成菱形
框架结构的飞机。作为一种飞行器创新布局,联结翼飞机具有较轻的重量、较高的刚度、较小的
诱导阻力和较大的升力系数等优点,是兼顾气动性能和结构效率折衷方案的一种较佳的布局型式。
联结翼机翼结构由于前后翼存在耦合作用,使结构的优化设计变得比较复杂。目前对于联结
翼的研究,探讨与总体布局相关的工作较多,而对结构细节设计方面的研究较少,且大多是金属
结构,复合材料结构很少。本文采用分步实现的优化策略,进行了在多种工况和不同约束条件下
联结翼复合材料机翼结构优化设计,探讨了刚度分配和有关参数对于机翼结构重量的影响。
本文提出分步实现的优化策略。首先,在应力、应变和位移约束下,以结构重量最轻为目标,
进行优化设计,确定蒙皮的铺层尺寸;第二步:优化设计梁的缘条和长桁的尺寸,使整个机翼结
构既满足强度和刚度要求,又满足稳定性要求。
采用分步优化设计的策略,分别研究了联结板高度、联结刚度、许用翼尖扭转角、稳定性以
及蒙皮 0 度层方向角对结构重量的影响。

关键词:联结翼,复合材料结构,结构优化,分步优化,重量特性
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联结翼复合材料机翼结构优化设计与重量特性分析
Abstract
The Joined-wing aircraft maybe defined as an aircraft that incorporates tandem wings to form
diamond shapes, in which forewing is aft swept with positive-dihedral angle and rear-wing is forward
swept with negative-dihedral angle. As an innovative aircraft configuration, Joined-wing has many
advantages, such as lighter weight, higher stiffness, lower induced drag and bigger lift coefficient. It is a
better configuration both in aerodynamics and structure than traditional configuration.
posite structure of joined-wing is intricate for optimal design because of the coupling
between the forewing and rear-wing. The work of joined-wing concentrated more on layout and metal
materials, and less on the details of structural design posite materials. A two-step optimization
technology was proposed in this thesis to achieve the analysis and design, in which 16 load cases and
different constrains were included. The effects of the stiffness distribution and the joint parameters on
structural weight were investigated systematically.
Firstly, the thickness posite laminates was optimized in the proposed two-step optimization
technology, in which the structural weight was taken as the objective function, and stress、strain and
displacement constrains were included. Then the dimensions of the st