The Effects of Ply Orientation on Nonlinear Buckling of Aircraft composite Stiffened Panel-Reference-Cited by-同舟云学术

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

2. 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

3. 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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