Buckling Load Maximization of Curvilinearly Stiffened Tow-Steered Laminates
Author:
Affiliation:
1. Virginia Polytechnic Institute and State University, Blacksburg, Virginia 24061
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Reference17 articles.
1. Optimum stacking sequence design of composite materials Part II: Variable stiffness design
2. Surrogate-based multi-objective optimization of a composite laminate with curvilinear fibers
3. Design of variable-stiffness composite panels for maximum buckling load
4. Optimization of Tow-Steered Composite Wing Laminates for Aeroelastic Tailoring
5. Variable stiffness composite panels: Effects of stiffness variation on the in-plane and buckling response
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1. Experimental and numerical studies on buckling and post-buckling behavior of T-stiffened variable stiffness panels;Chinese Journal of Aeronautics;2024-08
2. Buckling optimization of variable stiffness composite wing boxes with manufacturing defects;Structural and Multidisciplinary Optimization;2024-06-22
3. Design Framework for Optimization of Curvilinearly Stiffened Variable Stiffness Composite Laminates with Direct Fiber Angle Parameterization;AIAA SCITECH 2024 Forum;2024-01-04
4. Deterministic and probabilistic buckling response of fiber–metal laminate panels under uniaxial compression;Aircraft Engineering and Aerospace Technology;2021-12-28
5. Buckling Optimization of Variable Stiffness Composite Panels for Curvilinear Fibers and Grid Stiffeners;Journal of Composites Science;2021-12-15
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