Publication: Computational analysis of temperature effect in composite bolted joints for aeronautical applications
Identifiers
ISSN: 0731-6844 (Print)
ISSN: 1530-7964 (Online)
Publication date
2011-01
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Publisher
SAGE Publications
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Abstract
This study focuses on the analysis of influence of temperature and bolt torque on aeronautical joint behavior. A single-lap joint, according to ASTM D5961, with a titanium bolt and composite plates was considered. A numerical model based on FEM was developed to evaluate the stress in both bolt and composite plates. Load–displacement curves, stress fields, and induced damage showed, significantly, the influence of temperature combined with torque level on the joint. It was found that in the plate, both maximum and minimum levels of torque considered produced damage above critical threshold. This fact should be accounted for, during the design process of the joint.
Description
Keywords
Aeronautical structures, Finite element modeling, Composite joint, Thermo-mechanical load
Bibliographic citation
Journal of Reinforced Plastics and Composites, (Jan. 2011), 30(1), 3-11.