Analysis of compression stability and load capacity of thick composite plate structures
-
摘要:
针对复合材料厚板压缩稳定性分析问题进行了研究。对复合材料机身厚板结构进行压缩试验，试验中发现长桁底部蒙皮先发生屈曲，长桁未起到隔波作用；对该结构采用有限元线性和非线性分析方法进行分析，分析结果验证了该屈曲特征。根据试验和分析结果对稳定性分析方法进行了修正，采用修正的分析方法计算得到的屈曲载荷和承载能力精度更高，为复合材料厚板结构的屈曲分析和承载能力计算提供了一种新的方法。
Abstract:The compression stability of composite thick plates was studied. Firstly, the compression test was carried out on the thick plate structure of the composite fuselage. It was found that the bottom skin of the stringer was buckling first, and the stringer did not play the role of wave isolation. Secondly, the finite element linear and nonlinear analysis methods were carried out on the structure. The he buckling characteristics was verified. Finally, the stability analysis method was revised according to the test and analysis results. The buckling load and bearing capacity calculated by the modified analysis method were more accurate. A new method for buckling analysis and load-bearing capacity calculation of composite thick plate structures was established.
-
Key words:
- composite /
- stiffened plates /
- thick plate /
- stability /
- load capacity /
- transverse shear
-
图 4 试验件截面应变片编号示意图
Figure 4. Schematic diagram of section strain gauge numbering for test specimen
图 5 T型长桁壁板压缩试验件加载示意图
Figure 5. Schematic diagram of loading of T-shaped stiffened panel compression test specimen
图 6 考核区蒙皮应变片载荷应变曲线
Figure 6. Load-strain curves of skin strain gauges in the examination area
图 8 T型长桁壁板压缩试验件有限元模型示意图
Figure 8. Schematic diagram of finite element model of T-shaped stiffened compression test specimen
图 13 加筋壁板试件截面尺寸示意图
Figure 13. Schematic diagram of cross-section dimensions of stiffened panel
图 14 轴压作用下四边简支矩形平板
Figure 14. Rectangular plate simply supported on four sides under axial compression
图 15 等效蒙皮宽度定义示意图
Figure 15. Schematic diagram of definition of effective skin width of stiffened panel
图 16 复材柱失稳类型与长细比关系
Figure 16. Relationship between instability type and slenderness ratio of composite columns
表 1 材料属性
Table 1. Material properties
材料 E11/MPa E22/MPa G12/MPa μ12 M21C/IMA 148000 9650 4600 0.31 
下载: 导出CSV
表 2 壁板结构复材部分铺层信息
Table 2. Layups for composite parts of stiffened panel
部位 铺层顺序 蒙皮考核区 [45,−45,0,45,−45,90,0,45,90,−45,45,
−45,0,45,90,−45,45,90,−45,0]s蒙皮过渡段 [45,−45,0,45,−45,90,−45,0,45,−45,90,45,−45,
90,45,−45,0,45,90,−45,45,0,90,45,0,90,−45,0]s长桁腹板 [45,0,0,90,0,−45,0,−45,0,45]s 长桁缘条 [45,0,0,90,0,−45,0,−45,0,45,−45,0,45]
下载: 导出CSV
表 3 试验结果分析
Table 3. Analysis of test results
应变片编号 拐点处应变/με 拐点处载荷/kN B-5 2 587 1 324 B-10 2 584 1 331 B-8 2 188 1 264
下载: 导出CSV
表 4 分析结果与试验结果对比
Table 4. Compare calculation results with test results
方法 类型 载荷/kN 误差/% 试验 屈曲载荷 1264 破坏载荷 1492 工程 屈曲载荷（修正前） 1624 28.50 屈曲载荷（修正后） 1255 −0.70 柱失稳载荷（不考虑横向剪切） 2384 59.80 柱失稳载荷（考虑横向剪切） 1273 −14.70 有限元分析 线性分析 1370 8.40 非线性分析 1319 4.40
下载: 导出CSV
-
[1] KASSAPOGLOU C. Design and analysis of composite structures[M]. New York: Wiley, 2013: 237-273. [2] 王菲菲, 崔德刚, 熊强, 等. 复合材料加筋板后屈曲承载能力工程分析方法[J]. 北京航空航天大学学报, 2013, 39(4): 494-497.WANG F F, CUI D G, XIONG Q, et al. Engineering analysis of post-buckling loading capability for composite stiffened panels[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(4): 494-497(in Chinese). [3] 李乐坤, 李曙林, 常飞, 等. 复合材料加筋壁板压缩屈曲与后屈曲分析[J]. 南京航空航天大学学报, 2016, 48(4): 563-568.LI L K, LI S L, CHANG F, et al. Buckling and post-buckling of composite stiffened panel under compression[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2016, 48(4): 563-568(in Chinese). [4] 谭翔飞, 何宇廷, 冯宇, 等. 航空复合材料加筋板剪切稳定性及后屈曲承载性能[J]. 复合材料学报, 2018, 35(2): 320-331.TAN X F, HE Y T, FENG Y, et al. Stability and post-buckling carrying capacity of aeronautic composite stiffened panel under shear loading[J]. Acta Materiae Compositae Sinica, 2018, 35(2): 320-331(in Chinese). [5] 高志刚, 冯宇, 马斌麟, 等. 航空复合材料加筋板压缩屈曲及后屈曲力学性能[J]. 航空材料学报, 2020, 40(1): 53-61.GAO Z G, FENG Y, MA B L, et al. Compressive bucking and post-bucking mechanical properties of aeronautic composite stiffened panel[J]. Journal of Aeronautical Materials, 2020, 40(1): 53-61(in Chinese). [6] 王彬文, 张长兴, 郭文杰, 等. 考虑屈曲的复合材料加筋壁板铺层顺序优化[J]. 复合材料学报, 2021, 38(12): 4123-4137.WANG B W, ZHANG C X, GUO W J, et al. Stacking sequence optimization of composite stiffened panel considering buckling[J]. Acta Materiae Compositae Sinica, 2021, 38(12): 4123-4137(in Chinese). [7] 王燕, 李书, 许秋怡, 等. 复合材料加筋板剪切后屈曲分析与优化设计[J]. 航空学报, 2016, 37(5): 1512-1525.WANG Y, LI S, XU Q Y, et al. Optimization design and analysis of stiffened composite panels in post-buckling under shear[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(5): 1512-1525(in Chinese). [8] STAMATELOS D G, LABEAS G N, TSERPES K I. Analytical calculation of local buckling and post-buckling behavior of isotropic and orthotropic stiffened panels[J]. Thin-Walled Structures, 2011, 49(3): 422-430. [9] BACCIOCCHI M, TARANTINO A M. Analytical solutions for vibrations and buckling analysis of laminated composite nanoplates based on third-order theory and strain gradient approach[J]. Composite Structures, 2021, 272: 114083. [10] DHURVEY P, MITTAL N D. Buckling behavior of an orthotropic composite laminate using finite element analysis[J]. International Journal of Scientific Engineering and Technology, 2012, 1(4): 93-95. [11] PAIK J K, SEO J K. Nonlinear finite element method models for ultimate strength analysis of steel stiffened-plate structures under combined biaxial compression and lateral pressure actions—Part II: Stiffened panels[J]. Thin-Walled Structures, 2009, 47(8-9): 998-1007. [12] TAKANO A. Buckling test of CFRP cylindrical shells under compression load[J]. Journal of the Japan Society for Aeronautical and Space Sciences, 2018, 66(4): 98-111. [13] 石经纬, 赵娟, 刘传军, 等. 复合材料翼面壁板轴压稳定性[J]. 复合材料学报, 2020, 37(6): 1321-1333.SHI J W, ZHAO J, LIU C J, et al. Stability of composite stiffened panels under compression[J]. Acta Materiae Compositae Sinica, 2020, 37(6): 1321-1333(in Chinese). [14] 万华亮, 龚伟明, 覃俊娥. 复合材料帽型加筋壁板轴压稳定性研究[J]. 强度与环境, 2019, 46(1): 31-34.WAN H L, GONG W M, QIN J E. Research on the buckling and post-buckling behavior of hat-stiffened composite panels under axial compressive load[J]. Structure & Environment Engineering, 2019, 46(1): 31-34(in Chinese). [15] 葛建彪. 复合材料加筋壁板稳定性及承载能力分析[D]. 南京: 南京航空航天大学, 2010.GE J B. Stability and bearing capacity analysis of composite stiffened panel[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010(in Chinese). [16] STEVENS K A, RICCI R, DAVIES G A O. Buckling and postbuckling of composite structures[J]. Composites, 1995, 26(3): 189-199. [17] KONG C W, LEE I C, KIM C G, et al. Postbuckling and failure of stiffened composite panels under axial compression[J]. Composite Structures, 1998, 42(1): 13-21. [18] SHI G, XIONG Y. Probabilistic buckling analysis of fiber metal laminates under shear loading condition[J]. Advances in Engineering Software, 2000, 31(8): 519-527. [19] MISHRA B B, KUMAR A, SAMUI P, et al. Buckling of laminated composite skew plate using FEM and machine learning methods[J]. Engineering Computations, 2021, 38(1): 501-528. [20] VON KÁRMÁN T, TSIEN H S. The buckling of thin cylindrical shells under axial compression[M]. Amsterdam: Elsevier, 2012: 165-181. [21] STEIN M. Some recent advances in the investigation of shell buckling[J]. AIAA Journal, 1968, 6(12): 2339-2345. [22] 李真, 王俊, 邓凡臣, 等. 复合材料机身壁板的强度分析与试验验证[J]. 航空学报, 2020, 41(9): 118-130.LI Z, WANG J, DENG F C, et al. Strength analysis and test verification of composite fuselage panels[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(9): 118-130(in Chinese). [23] 陈庆远. 复合材料薄壁结构的屈曲和后屈曲分析[D]. 上海: 上海交通大学, 2015.CHEN Q Y. Buckling and post-buckling analysis of composite thin-walled structures[D]. Shanghai: Shanghai Jiao Tong University, 2015(in Chinese). [24] LI Z C, XIE Y G. Buckling mechanism of thin-walled arches with composite polyhedral shapes[J]. Composite Structures, 2021, 271: 114134. [25] EINAFSHAR N, LEZGY-NAZARGAH M, BEHESHTI-AVAL S B. Buckling, post-buckling and geometrically nonlinear analysis of thin-walled beams using a hypothetical layered composite cross-sectional model[J]. Acta Mechanica, 2021, 232(7): 2733-2750. [26] CHANG K, JENSEN J, MATTHEWS R, et al. Buckling strength of carbon/carbon panels[C]//Proceedings of the 31st Structures, Structural Dynamics and Materials Conference. Reston: AIAA, 1990. [27] 王勖成. 有限单元法[M]. 北京: 清华大学出版社, 2003: 649-651.WANG X C. Finite element method[M]. Beijing: Tsinghua University Press, 2003: 649-651(in Chinese). [28] 中国航空研究院. 复合材料结构稳定性分析指南[M]. 北京: 航空工业出版社, 2002: 5-11.China Aviation Research Institute. Guide to structural stability analysis of composite materials[M]. Beijing: Aviation Industry Press, 2002: 5-11(in Chinese). [29] VON KÁRMÁN T, SECHLER E E, DONNELL L H. The strength of thin plates in compression[J]. Journal of Fluids Engineering, 1932, 54(2): 53-56. [30] 牛春匀. 实用飞机结构应力分析及尺寸设计[M]. 冯振宇, 程小全, 张纪奎, 译. 北京: 航空工业出版社, 2009: 394-395.NIU C Y. Airframe stress analysis and sizing[M]. FENG Z Y, CHENG X Q, ZHANG J K , Translated. Beijing: Aviation Industry Press, 2009: 394-395(in Chinese). -
下载:
点击查看大图
计量
- 文章访问数: 1069
- HTML全文浏览量: 359
- PDF下载量: 84
- 被引次数: 0
