Load transfer in hybrid (bonded/bolted) composite single-lap joints

被引:194
作者
Kelly, G [1 ]
机构
[1] Kungl Tekniska Hogskolan, Dept Aeronaut & Vehicle Engn, Div Lightweight Struct, S-10044 Stockholm, Sweden
关键词
composite; single-lap joint; hybrid (bonded/bolted; finite element analysis;
D O I
10.1016/j.compstruct.2004.04.016
中图分类号
O3 [力学];
学科分类号
08 ; 0801 ;
摘要
The load transfer in hybrid (bolted/bonded) joints is complicated due to the difference in stiffness of the alternative load paths. The load distribution in hybrid composite single-lap joints has been predicted through use of a three-dimensional finite element model including the effects of bolt-hole contact and non-linear material behaviour. The effect of relevant joint design parameters on the load transferred by the bolt have been investigated through a finite element parameter study. Joint configurations where hybrid joining can provide improved structural performance in comparison to adhesive bonding have been identified. Experiments were performed to measure the distribution of load in a hybrid joint. A joint equipped with an instrumented bolt was used to measure the load transfer in the joint. The measured bolt load values were compared to predictions from the finite element model and the results were found to be in good agreement. (c) 2004 Published by Elsevier Ltd.
引用
收藏
页码:35 / 43
页数:9
相关论文
共 9 条
[1]  
ASTM, 2002, D. 638-02a Standard Test Method for Tensile Properties of Plastics
[2]  
CHANDY D, 2001, PATIENT CARE, V35, P12
[3]  
CHI TT, 2002, P 10 EUR C COMP MAT
[4]   Fatigue of hybrid (adhesive/bolted) joints in SRIM composites [J].
Fu, MF ;
Mallick, PK .
INTERNATIONAL JOURNAL OF ADHESION AND ADHESIVES, 2001, 21 (02) :145-159
[5]  
Hart-Smith L, 1982, Technical report AFWAL-TR-81-3154
[6]   BONDED-BOLTED COMPOSITE JOINTS [J].
HARTSMITH, LJ .
JOURNAL OF AIRCRAFT, 1985, 22 (11) :993-1000
[7]  
*HIBB KARLSS SOR I, 2001, AB STAND US MAN V6 3
[8]   Three-dimensional stress analysis of bolted single-lap composite joints [J].
Ireman, T .
COMPOSITE STRUCTURES, 1998, 43 (03) :195-216
[9]  
PALMBERG B, 1991, 199109 FAA TN AER RE