，计算材料学
含金属预埋件碳纤维层合板在单向拉伸载荷
作用下的强度分析
张成雷
刘峰
（中国民航飞行学院航空工程学院，广汉618307）
文摘基于工程中金属预理件在复合材料层合板中的应用情况，建立了含圆柱形金属预埋件和含阶梯形金属预埋件碳纤维/环氧树脂层合板的三维分析模型。层合板中的单层板简化为三维正交各向异性材料。采用有限元方法对单向拉伸载荷下含金属预埋件层合板进行了应力分析，给出了单层板各主方向应力分布和金属预理件的VONMISES应力分布。基于复合材料单层板的最大应力强度准则给出了两种分析模型的极限载荷。分析结果表明，两种预埋件层合板模型的首次破坏均发生在90°铺层，破坏模式均为树脂基体拉伸断裂。圆柱形预埋件层合板的损伤位于中心孔边约12点钟位置，阶梯形预埋件层合板的损伤位于铺层与金属预埋件台阶面边缘约6点钟位置。由于不连续纤维含量较大，阶梯形预埋件的极限载荷比圆柱形预理埋件小 18.03%。
关键词碳纤维，复合材料，层合板，金属预埋件，强度分析
StrengthAnalysis.of CarbonFiberLaminatesWithPre-EmbeddedMetalPart
UnderUnidirectionalTensileLoad
Liu Feng
Zhang Chenglei
( Aviation Engineering Institute, Civil Aviation Flight University of China, Guanghan618307）
Abstract The analysis models of carbon fiber reinforced epoxy laminates with cylindrical and step shape pre-embedded metal part are built based on the application of embedded metal part in composite laminates. The single layer in the laminates is assumed as three dimensional orthotropic material. The stress analysis of the laminates with embedded metal part is carried out by finile element method. The distributions of material principal direction stress of the single layers and the von mises stress of metal part are given. The ultimate loads of the composite laminates are determined based on the strength criterion of maximum stress. It is shown that the initial damages of the two models both occur in the 90°layer, and the damage mode is matrix cracking under tension. The initial damage of the lami-nates with cylindrical embedded metal part occurs at the twelve o' clock location of the central hole border, and the initial damage of the laminates with step shape embedded metal part occurs at the six o' clock location of the border between the No. 7 layer and the pre-embedded metal part. Owing to the more discontinuous carbon fibers, the ulti-mate load of the laminates with step shape metal part is smaller than that of the laminates with cylindrical metal part by18.03%.
Key wordsCarbon fiber,Composite material,Laminates,Pre-embedded metal part,Strength analysis 收稿日期：2011-01-12
基金项目：中国民用航空飞行学院自然科学基金资助（编号2008-20）
作者简介：刘峰，1977年出生，博士，副教投，硕士研究生导师，主要研究方向：飞机结构与强度，复合材料结构设计与分析，数值计算与计算机仿真，飞机结构维修。E-mail；lhjl999@sohu.com
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2012年第6期