Comparative behavior of single-bolted and dual-bolted lap joints

被引：5

作者：

Pratt, JD ^{[1
]}

Pardoen, G

机构：

[1] Hartwell Corp, Placentia, CA USA

[2] Univ Calif Irvine, Dept Civil & Environm Engn, Irvine, CA 92664 USA

来源：

JOURNAL OF AEROSPACE ENGINEERING | 2002年 / 15卷 / 02期

关键词：

aerospace engineering; aircraft; bolted joints; finite elements; nonlinear analysis;

D O I：

10.1061/(ASCE)0893-1321(2002)15:2(55)

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Nonlinear finite-element models that predict the load-elongation behavior of single- and dual-bolted conical-head bolted lap joints are developed, and the load-elongation predictions are compared with experimental test data. The study is conducted for several panel thicknesses with a 4.8 mm size fastener and 2024-T3 clad aluminum alloy panels. The model load-elongation predictions are in excellent agreement with experimental test data. The results show that (1) dual-bolted lap joint test results underpredict the strength of single-bolted lap joints; and (2) numerical models may reliably predict the load-elongation behavior of mechanically fastened lap joints at a fraction of the cost and time of experimental testing.

引用

页码：55 / 63

页数：9

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