Thereotical solutions of adhesive stresses in bonded composite butt joints

In this paper, closed-form solutions for the adhesive stresses in bonded composite single-strap butt joints have been obtained. Two strategies were used for deriving the adhesive peel stress. The solutions are applicable to a butt joint made from different adherend and doubler laminates, as well as the unbalanced single-lap joints. In addition, three-dimensional finite element models of the unit-width composite joints were created for analyzing the adhesive stresses under a plane strain condition. A total of six joint conditions, three joint configurations and each with two layup sequences, were studied. Consistency in the peel stress predictions was obtained from the two theoretical strategies. Good agreement has been achieved between the theoretical and finite element results. The effects of the doubler thickness and laminate layup sequence on the adhesive stress variation can be displayed. The theoretical solution would provide a solid foundation for supporting the practical composite joint assessment.

Keywords

adhesive stresses, closed-form solutions, composite single-strap butt joint, finite element analysis

Mathematical Subject Classification 2010

Primary: 00A05

Milestones

Received: 1 September 2011

Revised: 24 November 2011

Accepted: 13 January 2012

Published: 26 July 2012

Authors

Gang Li
Structures Group, Aerospace Portfolio National Reseach Council Canada M-3, 1200 Montreal Road Ottawa ON K1A 0R6 Canada

Vol. 7, No. 4, 2012

Gang Li

Abstract

Keywords

Mathematical Subject Classification 2010

Milestones

Authors