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The Effects of Ply Orientation on Nonlinear Buckling of Aircraft composite Stiffened Panel

  • Published:2019-08-10 Issue:50 Volume:13 Page:126-140
  • ISSN:1971-8993
  • Container-title:Frattura ed Integrità Strutturale
  • language:
  • Short-container-title:

Author:

Mouhat Ouadia1,Bybi Abdelmajid2,El Bouhmidi Ahmed3,Rougui Mohamed3

Affiliation:

1. Mohammed V University, Structure LGCE l’EST, Salé -CED de l’EMI, Rabat, Morocco

2. Mohammed V University in Rabat, EST Sale - Morocco MEAT - Materials Energy Acoustics Team-CED of Mohammadia Engineering School, Rabat.

3. Mohammed V University, Structure LGCE, EST Sale -CED of Mohammadia Engineering School, Rabat, Morocco.

Publisher

Gruppo Italiano Frattura

Subject

Mechanical Engineering,Mechanics of Materials

Cited by 4 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Buckling characteristics of nano‐silica doped carbon fiber reinforced composites having cutouts;Polymer Composites;2024-03-05

2. Investigation on nonlinear buckling performance of the optimized wing structure under the realistic flight cases;Aerospace Science and Technology;2023-08

3. Buckling behavior of laminated composite stiffened cylindrical shell panels having cutout for different parametric variations;Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science;2022-05-27

4. Buckling characteristics of cut-out borne composite stiffened hyperbolic paraboloid shell panel;Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications;2021-05-06
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