Prebuckling and Buckling of Unsymmetrically Laminated Composite Panels with Stringer Run-Outs
Author:
Affiliation:
1. Airbus Operations, Ltd., Bristol, England BS34 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/10.2514/1.44665
Reference18 articles.
1. On the calculation of energy release rates for cracked laminates
2. Buckling and postbuckling of composite structures
3. Delamination Growth in Composites under Cyclic Loads
4. The Behavior of Compressively Loaded Stiffener Runout Specimens – Part II: Finite Element Analysis
5. Nonlinear Analytical Approach for Preliminary Sizing of Discrete Composite Stringer Terminations
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3. RAPID analysis of variable stiffness beams and plates: Legendre polynomial triple-product formulation;International Journal for Numerical Methods in Engineering;2017-04-03
4. Buckling and Postbuckling of Stiffened Composite Panels with Cracks and Delaminations by Ritz Approach;AIAA Journal;2017-03
5. Debond Resisting Composite Stringers;53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference<BR>20th AIAA/ASME/AHS Adaptive Structures Conference<BR>14th AIAA;2012-04-23
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