法向载荷下含金属预埋件碳纤维层合板强度分析

复合材料科学与工程 ›› 2013, Vol. 0 ›› Issue (7): 19-23.

法向载荷下含金属预埋件碳纤维层合板强度分析

刘峰, 张中波, 张成雷^*

中国民用航空飞行学院航空工程学院,广汉 618307

收稿日期:2013-03-14 出版日期:2013-10-28 发布日期:2022-03-15
通讯作者: 张成雷(1988-),男,硕士研究生,caihaha888@126.com。
作者简介:刘峰(1977-),男,博士,副教授,硕士研究生导师,主要研究方向为飞机结构与强度,复合材料结构设计与分析。
基金资助:
国家自然科学基金民航联合基金重点项目(U1233202/F01); 中国民航飞行学院科研基金(2008-20); 民航局科技项目重大专项(MHRD201240)

STRENGTH ANALYSIS OF CARBON FIBER LAMINATES WITH PRE-EMBEDDED METAL PART UNDER MORMAL LOAD

LIU Feng, ZHANG Zhong-bo, ZHANG Cheng-lei^*

College of Aeronautical Engineering,Civil Aviation Flight University of China,Guanghan 618307,China

Received:2013-03-14 Online:2013-10-28 Published:2022-03-15

摘要/Abstract

摘要： 建立了含圆柱形金属预埋件和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,单层板简化为三维正交各向异性材料。采用有限元方法对法向载荷下含金属预埋件四边简支层合板进行了应力分析,给出了发生初始损伤单层板各材料主方向应力分布和金属预埋件的VON MISES 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,含圆柱形预埋件层合板初始损伤发生在45°铺层靠近孔边的2点钟方位,破坏模式为基体剪切破坏;含阶梯型预埋件层合板初始损伤发生在–45°铺层靠近孔边的10点钟方位,破坏模式为基体拉伸破坏。法向载荷作用下,阶梯型预埋件结构比圆柱形预埋件结构具有更大的传力面积,大部分纤维处于适宜的受拉状态,其极限载荷比圆柱形预埋件结构提高了40.36%。

关键词: 碳纤维, 复合材料, 层合板, 金属预埋件, 强度分析

Abstract: The analysis models of carbon fiber reinforced epoxy laminates with cylindrical and step shape preembedded 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 which is simply supported is carried out by finite element method. The distributions of material principal direction stresses of the damaged single layers and the von mises stress of metal parts 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 damage of the laminates with cylindrical shape pre-embedded metal part occurs at about two o'clock location near the central hole border in the 45° layer, and the damage mode is matrix crack under shearing. The initial damage of the laminates with step shape pre-embedded metal part occurs at about ten o'clock location near the central hole border in –45° layer. Under normal loading, the ultimate load of the laminates increases by 40. 36% when the cylindrical metal part is replaced by the step metal part, which is due to the increase of the force transfer area and bigger percentage of fibers under desirable tension state.

Key words: carbon fiber, composite material, laminates, pre-embedded metal part, strength analysis

中图分类号:

TB332
TB333

刘峰, 张中波, 张成雷. 法向载荷下含金属预埋件碳纤维层合板强度分析[J]. 复合材料科学与工程, 2013, 0(7): 19-23.

LIU Feng, ZHANG Zhong-bo, ZHANG Cheng-lei. STRENGTH ANALYSIS OF CARBON FIBER LAMINATES WITH PRE-EMBEDDED METAL PART UNDER MORMAL LOAD[J]. COMPOSITES SCIENCE AND ENGINEERING, 2013, 0(7): 19-23.

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