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Behaviour of composite wing T‐joints in hygrothermal environments

Behaviour of composite wing T‐joints in hygrothermal environments This paper deals with the experimental investigation and non‐linear finite element analysis of composite wing T‐joints in hygrothermal environments. This study is concerned with T‐joints subjected to tension (pull‐out) force and their behaviour up to ultimate failure under bone dry and hygrothermal environments. The behaviour of such joints is complex due to the geometry of the joint configuration and laminated construction. T‐joints are also susceptible when exposed to moisture and temperature environments. As a consequence, the stiffness and strength properties of laminates because degraded. A three‐dimensional 20‐noded multidirectional composite element is developed using three‐dimensional super element concept to analyse both unstitched and stitched T‐joints. All the stress components are computed and the failure loads are evaluated using different failure criteria to get better insight into the behaviour of laminated composite wing T‐joints. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Behaviour of composite wing T‐joints in hygrothermal environments

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References (25)

Publisher
Emerald Publishing
Copyright
Copyright © 2004 Emerald Group Publishing Limited. All rights reserved.
ISSN
0002-2667
DOI
10.1108/00022660410545528
Publisher site
See Article on Publisher Site

Abstract

This paper deals with the experimental investigation and non‐linear finite element analysis of composite wing T‐joints in hygrothermal environments. This study is concerned with T‐joints subjected to tension (pull‐out) force and their behaviour up to ultimate failure under bone dry and hygrothermal environments. The behaviour of such joints is complex due to the geometry of the joint configuration and laminated construction. T‐joints are also susceptible when exposed to moisture and temperature environments. As a consequence, the stiffness and strength properties of laminates because degraded. A three‐dimensional 20‐noded multidirectional composite element is developed using three‐dimensional super element concept to analyse both unstitched and stitched T‐joints. All the stress components are computed and the failure loads are evaluated using different failure criteria to get better insight into the behaviour of laminated composite wing T‐joints.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Aug 1, 2004

Keywords: Aircraft; Non‐linear control systems; Damping; Stress (materials); Composite materials; Laminates

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