复合材料变厚度加筋板后屈曲耐久性/损伤容限一体化设计研究  

Study of Post-Buckling Durability/Damage Tolerance Design of Variable Thickness Composite Stiffened Panel

作　　者：李戈岚[1] 吴斌[1] 

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞机设计》2007年第5期24-30,共7页Aircraft Design

摘　　要：在先进的复合材料飞机结构上大量采用复合材料加筋板这种结构形式。因此,本文着重研究了复合材料变厚度加筋板后屈曲、冲击损伤与冲击损伤对承载能力的影响,以及复合材料变厚度加筋板冲击损伤、后屈曲、耐久性/损伤容限设计一体化综合试验方法。最后,作者根据多年从事飞机型号结构设计经验,并结合本文的研究结果,总结出15项复合材料变厚度加筋板后屈曲耐久性/损伤容限一体化设计技术,以期对我国预研新机的复合材料飞机结构设计,对已研飞机的复合材料飞机结构改进、评定有所启示。Composite stiffened skin panels are broadly used in advanced composites aircraft structure. In this paper, a study of post buckling, impact damage, and influence of impact damage on the load carrying capacity of composite stiffened panel, a synthetic test method for impact damage, post-buckling, and durability/damage tolerance design of variable-thickness composite stiffened panels is pro-posed. 15 design techniques for post-buckling durability/damage tolerance of variable-thickness composite stiffened panels are summarized from multiple past airframe structure design experiences and thisstudy effort to provide a design tool for future composite airframe structure design and the modification of current composite airframe structures.

关 键 词：复合材料加筋板 变厚度 后屈曲 冲击损伤 承载能力 耐久性/损伤容限设计 一体化综合试验方法 

分 类 号：V257[一般工业技术—材料科学与工程]