Stress Distribution on Composite Honeycomb Sandwich Structure Suffered from Bending Load
The use of honeycomb sandwich structure is increasing rapidly due to their excellence strength to weight and stiffness to weight characteristics.They are widely used in aircrafts,ships,and bridges industries et.al.The strength of honeycomb sandwich structure is a combination property of the skin,core and core-skin interfacial bonding.Any weak point in the three elements will reduce the performance of the structure.At present the skin of the sandwich structure is made of rigid fiber reinforce plastic composite,however,honeycomb cores are made of aluminum foil,Nomex paper.As a result mechanical performance of the sandwich structure is restricted by the honeycomb core.Recently,some papers reported composite sandwich structures with fibre/plastic composite cores have better mechanical performance than traditional sandwiches.Jian Xiong and Ashkan Vaziri studied the specific energy absorption of composite pyramidal-core sandwich panels.They found that composite which made of two-layer carbon fibre composite pyramidal truss cores have better specific energy absorption.Tochukwu George,Vikram S.Deshpande prepared Carbon fiber reinforced polymer(CFRP)composite sandwich panels with hybrid foam filled CFRP pyramidal lattice cores.They found sandwich with hybrid foam filled CFRP pyramidal lattice cores also have better energy absorption property than traditional structures.Lu Che and Guo-dong Xu et.al prepared an octahedral stitched sandwich using stitched composite cores.Results indicated that octahedral stitched composite core exhibited higher specific shear stiffness/strength and out-of-plane compressive strength than conventional sandwich cores,but showed lower compressive stiffness.Although composite pyramidal-core,pyramidal lattice cores or stitched composite cores can increase structure energy absorption property,but their improvement on composite bending performance is not so significant.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.
Honeycomb sandwich structure Damage Finite element Method Composite
Chun Lu Mingyue Zhao Liu Jie Jing Wang Yu Gao Xu Cui Ping Chen
Liaoning Key Laboratory of General Aviation & Liaoning Key Laboratory of Composite Manufacture techn Haerbin Aircraft Industrial(Group)Co.,Ltd. Haerbin Heilongjiang,China 150066 State Key Laboratory of Materials Modification by Beams & School of Chemical Engineering,Dalian Univ
国际会议
2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)
上海
英文
1-8
2014-09-24（万方平台首次上网日期，不代表论文的发表时间）