ON DESIGN METHODS FOR BOLTED JOINTS IN COMPOSITE AIRCRAFT STRUCTURES

被引：35

作者：

IREMAN, T

NYMAN, T

HELLBOM, K

机构：

[1] Saab Military Aircraft

来源：

COMPOSITE STRUCTURES | 1993年 / 25卷 / 1-4期

关键词：

D O I：

10.1016/0263-8223(93)90205-5

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

The problems related to the determination of the load distribution in a multi-row fastener joint using the finite element method are discussed. Both simple and more advanced design methods used at Saab Military Aircraft are presented. The stress distributions obtained with an analytically based method and an FE-based method are compared. Results from failure predictions with a simple analytically based method and the more advanced FE-based method of multi-fastener tension and shear loaded test specimens are compared with experiments. Finally, complicating factors such as three-dimensional effects caused by secondary bending and fastener bending are discussed and suggestions for future research are given.

引用

页码：567 / 578

页数：12

共 32 条

[1]

AGERWAL BL, 1979, 20TH AIAA ASME ASCE, P303

[2]

ARNOLD WS, 1989, COMPOS STRUCT, V13, P133

[3] POST-FAILURE ANALYSIS OF BOLTED COMPOSITE JOINTS IN TENSION OR SHEAR-OUT MODE FAILURE [J].