Stress Analysis of In-Plane, Shear-Loaded, Adhesively Bonded Composite Joints and Assemblies
Abstract
Recent small aircraft that have been certified in the United States, such as the Cirrus SR2O and the Lancair Columbia 300, share similar structural attributes. Specifically, they are both of nearly all-composite construction and both make extensive use of adhesive bonding as a primary method for forming structural joints. Adhesive bonding has potential for being a simple and cost- effective means by which large built-up structures can be assembled. Challenges to bonding exist in the areas regarding adhesive selection, proper surface preparation, and technician training as well as intelligent design and confidence in analyses. This report addresses the latter challenge by presenting an analysis methodology that can be used in the design of joints loaded in both tension and in-plane shear. Example calculations and applications to real structures are provided. A closed-form stress analysis of an adhesive-bonded lap joint subjected to spatially varying in-plane shear loading is presented. The solution, while similar to Volkersen's treatment of tension-loaded lap joints, is inherently two-dimensional and, in general, predicts a multicomponent adhesive shear stress state. Finite difference and finite element numerical calculations are used to verify the accuracy of the closed-form solution for a joint of semi-infinite geometry. The stress analysis of a finite-sized doubler is also presented. This analysis predicts the adhesive stresses at the doubler boundaries and can be performed independently from the complex stress state that would exist due to a patched crack or hole located within the interior of the doubler.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 2001
- Accession Number
- ADA392847
Entities
People
- Hyonny Kim
- Keith Kedward
Organizations
- University of California, Santa Barbara