Local buckling updating engineering method of hat-stiffened composite panel based on flexural stiffness ratio

被引：0
|
作者：
Zhang Q. [1 ]
Chen J. [1 ]
Kong B. [1 ,2 ]
Bai R. [3 ]
Huang X. [3 ]
Liu W. [3 ]
机构：
[1] AVIC Chengdu Aircraft Design and Research Institute, Chengdu
[2] State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing
[3] State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology, Dalian
来源：
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | 2022年 / 39卷 / 12期
关键词：
buckling; composites; flexural stiffness ratio; hat-stiffened panel; updating method;
D O I：
10.13801/j.cnki.fhclxb.20211216.001
中图分类号：
学科分类号：
摘要：
In order to improve the accuracy of local buckling engineering method of hat-stiffened composite panel, the stability experiment of typical panels under axial compression was first carried out, and then an updating engineering method for local buckling of hat-stiffened composite panel based on flexural stiffness ratio was proposed. The predicted buckling loads differ less than 3% from experimental results. The buckling analysis of two kinds of hat-stiffened panels with bottom flange was carried out by finite element model (FEM) method and the updating method this paper proposed comparatively. The error of compared results is within 10%, which verifies the reasonableness of the proposed method and satisfies the engineering accuracy. Experimental data recorded in public literature were analyzed by engineering simplified method, energy method and the updating method this paper proposed comparatively. Results show that the error by engineering simply and fixedly supported boundary conditions can be reduced from 41.5% and 5.3% to 3.8% respectively, which provides a new rapid analytical method for preliminary design of hat-stiffened composite panel. © 2022 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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页码：6109 / 6118
页数：9
相关论文
共 18 条
  • [1] YANG Naibin, ZHANG Yining, Composite aircraft structure design, (2002)
  • [2] CHRISTOS K., Design and analysis of composite structures with application to aerospace structures, (2011)
  • [3] LIU X, HAN K, BAI R, Et al., Buckling measurement and numerical analysis of M-type ribs stiffened composite panel[J], Thin-Walled Structures, 85, pp. 117-124, (2014)
  • [4] LI Lantian, ZHAO Xun, Reliability analysis of stiffened composite plates with multiple failure modes, Journal of Hunan University of Science & Technology (Natural Science Edition), 32, 2, pp. 52-57, (2017)
  • [5] CHEN Wei, XU Xiwu, Buckling and postbuckling response analysis of the doubly-curved composite shell by nonlinear FEM, Acta Materiae Compositae Sinica, 25, 2, pp. 178-187, (2008)
  • [6] KONG Bin, CHEN Puhui, CHEN Yan, Post-buckling failure evaluation method of integrated composite stiffened panels under uniaxial compression[J], Acta Materiae Compositae Sinica, 31, 3, pp. 765-771, (2014)
  • [7] LIU Congyu, XU Xiwu, CHEN Kang, Buckling, post-buckling and collapse analysis of stiffened composite panels with debonding damage[J], Acta Materiae Compositae Sinica, 27, 6, pp. 158-166, (2010)
  • [8] SHAO Qing, HE Yuting, ZHANG Teng, Et al., Influence of side boundary condition on buckling and post-buckling performance of composite stiffened panels under axial, Acta Materiae Compositae Sinica, 31, 3, pp. 741-748, (2014)
  • [9] SUN Zhonglei, ZHANG Guofan, LI Junpeng, Study on loading capacity of composite panels under uniaxial compression[J], Aeronautical Computing Technique, 46, 3, pp. 63-66, (2016)
  • [10] Aircraft design manual. 9th. Load, strength and stiffenss, (2001)
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