Research progress in post-buckling design and analysis techniques for composite stiffened panel

被引：0
作者：
Chen, Xiangming [1 ]
Li, Xinxiang [1 ]
Chai, Yanan [1 ]
Chen, Puhui [2 ]
Sun, Xiasheng [3 ]
机构：
[1] National Key Laboratory of Strength and Structural Integrity, Aircraft Strength Research Institute of China, Xi’an
[2] College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[3] School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai
来源：
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | 2024年 / 41卷 / 09期
基金：
中国国家自然科学基金;
关键词：
buckling; composites; engineering analysis; numerical analysis; post-buckling; stiffened panels;
D O I：
10.13801/j.cnki.fhclxb.20240611.003
中图分类号：
学科分类号：
摘要：
The large-scale application of composite materials is the main means of weight reduction for aircraft stiffened panel structures, but due to overly conservative design criteria, the weight reduction effect of the structure is not ideal. Thin-walled stiffened panel structures usually have a long post-buckling bearing history, but due to the lack of effective analysis methods for post-buckling design and evaluation, currently, aircraft composite stiffened panels almost do not allow the skin to buckle below the limited load, which cannot fully utilize the weight reduction characteristics of composite materials. This article reviewed the development process of stability design for composite stiffened panels and elaborates on the necessity of conducting post-buckling design analysis, and provided a detailed review of the research progress on the buckling and post-buckling performance analysis and design methods of stiffened panel structures, focusing on two aspects: engineering analysis technology and numerical analysis technology; Explored the main factors affecting the buckling and post-buckling performance of composite stiffened panels, and discussed the effects of buckling fatigue, damage/defects, and humid thermal environment on structural performance; Finally, the overall status of post-buckling design and analysis technology for composite stiffened panels was summarized, and future technological development trends were discussed. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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收藏
页码：4647 / 4674
页数：27
相关论文
共 180 条
  • [1] CUI Degang, Structure technology development of large commercial aircraft, Acta Aeronautica et Astronautica Sinica, 29, 3, pp. 573-582, (2008)
  • [2] DEGENHARDT R, CASTRO S G P, ARBELO M A, Et al., Future structural stability design for composite space and airframe structures, Thin-Walled Structures, 81, 7, pp. 29-38, (2014)
  • [3] HAO P, WANG B, TIAN K, Et al., Integrated optimization of hybrid stiffness stiffened shells based on sub-panel elements, Thin-Walled Structures, 103, pp. 171-182, (2016)
  • [4] GE D, MO Y, HE B, Et al., Experimental and numerical investigation of stiffened composite curved panel under shear and in-plane bending, Composite Structures, 137, pp. 185-195, (2016)
  • [5] GLISZCZYNSKI A, KUBIAK T., Progressive failure analysis of thin-walled composite columns subjected to uniaxial compression, Composite Structures, 169, pp. 52-61, (2017)
  • [6] ZIMMERMANN R, ROLFES R., POSICOSS-improved postbuckling simulation for design of fibre composite stiffened fuselage structures, Composite Structures, 73, pp. 171-174, (2006)
  • [7] DEGENHARDT R, ROLFES R, ZIMMERMANN R, Et al., COCOMAT-improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse, Composite Structures, 73, pp. 175-178, (2006)
  • [8] DEGENHARDT R, KLING A, ROHWER K, Et al., Design and analysis of stiffened composite panels including postbuckling and collapse, Computers and Structures, 86, pp. 919-929, (2008)
  • [9] FENG Yu, HE Yuting, SHAO Qing, Et al., Buckling and postbuckling performance of aeronautic composite stiffened panel under compression, Journal of Aerospace Power, 29, 12, pp. 2905-2913, (2014)
  • [10] MERT M, KAYRAN A., Post-buckling load redistribution of stiffened panels in aircraft wing box structures, 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, pp. 1-12, (2016)
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