Integration of Fatigue R-Curve Effects into VCCT for Durability Predictions, Part 1: Buckled Composite Single-Stringer Stiffened Panels
Author:
Affiliation:
1. Lockheed Martin Aeronautics Company
2. Lockheed Martin Aeronautics Co Marietta
Publisher
American Institute of Aeronautics and Astronautics
Link
https://arc.aiaa.org/doi/pdf/10.2514/6.2023-0952
Reference26 articles.
1. Li B, Gong Y, Gao Y, Hou M, and Li L, 2022, "Failure Analysis of Hat-Stringer-Stiffened Aircraft Composite Panels under Four-Point Bending Loading," Materials Vol. 15, No. 7.
2. A post-buckling compressive failure analysis framework for composite stiffened panels considering intra-, inter-laminar damage and stiffener debonding
3. Future structural stability design for composite space and airframe structures
4. Ge D, Mo Y, He B, Wu Y, and Du X, 2016, "Experimental and numerical investigation of stiffened composite curved panel under shear and in-plane bending," Composite Structures, Vol 137.
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