Nonlinear Analytical Approach for Preliminary Sizing of Discrete Composite Stringer Terminations
Author:
Affiliation:
1. Airbus UK, Ltd., Bristol, England BS99 7AR, United Kingdom
2. University of Bristol, Bristol, England BS8 1TR, United Kingdom
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.37745
Reference13 articles.
1. Approximate Nonlinear Analysis Method for Debonding of Skin/Stringer Composite Assemblies
2. Skin-stiffener interface stresses in tapered composite panel
3. The Behavior of Compressively Loaded Stiffener Runout Specimens – Part II: Finite Element Analysis
4. Stiffener debonding mechanisms in post-buckled CFRP aerospace panels
5. Fracture mechanisms and failure processes at stiffener run-outs in polymer matrix composite stiffened elements
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1. Comparing the effect of geometry and stiffness on the effective load paths in non-symmetric laminates;AIAA Scitech 2019 Forum;2019-01-06
2. Damage tolerance optimization of composite stringer run-out under tensile load;Composite Structures;2015-12
3. Compound joint: A novel design principle to improve strain allowables of FRP composite stringer run-outs;Composites Part A: Applied Science and Manufacturing;2010-04
4. Buckling of stiffened composite panels with stringer terminations;Journal of Mechanics of Materials and Structures;2009-12-31
5. Prebuckling and Buckling of Unsymmetrically Laminated Composite Panels with Stringer Run-Outs;AIAA Journal;2009-10
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