Affiliation:
1. Structures Research Section Sikorsky Aircraft Division (UTC) 6900 Main Street Stratford, CT 06601
Abstract
An approach is presented to calculate stresses at the skin-stiffener inter faces of composite stiffened panels. The skin and stiffener can have general anisotropic layup and the loading can be in-plane or out-of-plane as long as the in-plane stresses far from the flange edge can be at most linear in the out-of-plane direction. A stress-based en ergy minimization is used with a variational calculus derivation of the governing equa tions. All six stresses are determined at the skin-stiffener interface. Comparison of the present closed form solution with a finite element solution shows good agreement. The stresses determined with the present method are used in a failure criterion to predict onset of delamination. The effects of geometry and layup on the onset of delamination for various loadings are investigated and several trend curves useful for design applications are presented.
Subject
Materials Chemistry,Polymers and Plastics,Mechanical Engineering,Mechanics of Materials,Ceramics and Composites
Cited by
10 articles.
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1. Experimental and numerical analysis of repaired stiffened carbon fiber-reinforced plastics panels under compression;Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science;2017-05-26
2. Vibration and stability of laminated composite orthogrid plates;Journal of Reinforced Plastics and Composites;2016-03-02
3. Skin-Stiffened Structure;Design and Analysis of Composite Structures;2013-05-01
4. Modeling damage and load redistribution in composites under tension–tension fatigue loading;Composites Part A: Applied Science and Manufacturing;2011-11
5. Skin-Stiffened Structure;Design and Analysis of Composite Structures;2010-09-14