Optimal Design of Tow-Placed Fuselage Panels for Maximum Strength with Buckling Considerations
Author:
Affiliation:
1. Delft University of Technology, 2629 HS Delft, The Netherlands
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.40357
Reference16 articles.
1. Compression Buckling Response of Tailored Rectangular Composite Plates
2. Shear buckling response of tailored composite plates
3. The use of curvilinear fiber format in composite structure design
4. Optimization of tow fiber paths for composite design
5. In-plane response of laminates with spatially varying fiber orientations - Variable stiffness concept
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