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论文类型：会议论文
发表时间：2014-09-24
收录刊物：EI、CPCI-S、SCIE、Scopus
卷号：99
页面范围：405-412
关键字：Honeycomb sandwich structure; Damage; Finite element Method; Composite
摘要：In this paper, we prepared a kind of carbon fibre/matrix composite honeycomb using carbon fibre and epoxy resin with compression molding technique. Composite Honeycomb Sandwich was prepared by gluing composite honeycomb with composite panels. Mechanical performance of the Composite Honeycomb Sandwich was characterized using finite element analysis (FEA) and three point bending performance. Results indicate that when suffering from bending loads, stress concentration is located at the loading zone as well as supporting zone. When bending load increases to 7200N, cracks occur on the interface between honeycomb and composite panel, the failure mode is interfacial de bonding between honeycomb core and composite panel. Result of three-point bending performance indicates that composite honeycomb Sandwich breaks down when bending load increases to 6800N, which agrees with FEA results. Compared with traditional aluminum and Nomex honeycomb Sandwich, carbon fibre/epoxy Honeycomb Sandwich has higher bending strength. It can be used in aviation and aerospace industries. (C) 2015 The Authors. Published by Elsevier Ltd.