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  • 中国标准连:ISSN1005-2895
  • 续出版物号: CN 33-1180/TH
  • 主管单位:轻工业杭州机电设计研究院有限公司
  • 主办单位:轻工业杭州机电设计研究院有限公司、中国轻工机械协会、中国轻工业机械总公司
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  • 主  编:黄丽珍
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陈栋栋, 吴明格, 胡凯, 陈健.简支复合矩形对称层合板的近似分析法[J].轻工机械,2018,36(3):73-78
简支复合矩形对称层合板的近似分析法
Approximate Analysis of Simple Support Symmetric Rectangular Laminated Plates
  
DOI:10.3969/j.issn.1005 2895.2018.03.014
中文关键词:  对称层合板  不同长宽比  解析解  有限元法  正交长层合板近似  正交层合板近似
英文关键词:symmetric laminated  different aspect ratio  exact solutions  FEM(finite element method)  OLA(orthotropic long plate laminate approximation)  OA(orthotropic laminated plate approximation)
基金项目:浙江省教育厅科研基金(Y201737452)
作者单位
陈栋栋, 吴明格, 胡凯, 陈健 浙江省特种设备检验研究院 浙江 杭州310020 
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中文摘要:
      为了研究一般简支对称层合板近似求法适用性问题,依据Ritz法、最小势能原理经代数转化获得便于MATLAB编程的力学解析解;不同长宽比AR与 铺层角度θ下,正交与10%原则设计层合板通过有限元法(FEM)、正交长层合板近似(OLA)、正交层合板近似(OA)得到值和解析解对比。结果表明:FEM法 与解析解中面最大位移值w0误差在5%以内,随AR增大,两者误差趋于稳定并一致;正交板在低弯曲刚度D11下,OLA法在临界AR处 w0误差达294.4%,而大AR下,OLA与解析解结果一致;10%原则板在AR大于3时,FEM和OA法得到w0与解析解一致,AR小于3时,两近 似法符合工程需求,但大弯扭耦合D16,D26下,在AR=1,2,θ=90°时,误差为10.98%,8.67%,相较于解析解有较大误差。研究 结果为复合材料结构设计阶段提供了一定的参考。
英文摘要:
      In order to analyze the approximate applicability of general simple supported symmetric laminated plates, according to the Ritz method and the minimum potential energy principle, the closed form solution of the laminated plates was obtained after the algebraic manipulations and matrix transformation, which was convenient for MATLAB programming. Values about the orthotropic laminate and the 10% rule laminate, obtained through the orthotropic laminated plate approximation (OA), the finite element method (FEM), the orthotropic long plate laminate approximation (OLA), were compared with the value of exact solution, under different aspect ratio AR and ply angle θ.The result shows that maximum displacement w0 of FEM is within 5% errors compared with exact solution. As the aspect ratio AR increases, the error tends to be stable and consistent. Under the low bending stiffness D16, OLA w0 at the critical AR is 294.4% errors compared with exact solution about the orthotropic laminate, while w0 is consistent at the large AR ratio. For the 10% rule laminates, as AR is getting greater than 3, FEM w0 and OA w0 are consistent with the exact solution, and as AR getting less than 3, the w0 from the prior approximate methods meets the engineering requirements, however, error is large when under the large bending twist coupling stiffness D16, D26, at AR=1 and 2 with θ=90°, the OA w0 are 10.98% and 8.67% errors compared with the exact solution w0. The research has certain directive significance on the design of composite structure.
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