Volume 30 Issue 09
Sep.  2004
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Xiu Yingshu, Cui Degang. Optimal design of composite sandwich structure[J]. Journal of Beijing University of Aeronautics and Astronautics, 2004, 30(09): 855-858. (in Chinese)
Citation: Xiu Yingshu, Cui Degang. Optimal design of composite sandwich structure[J]. Journal of Beijing University of Aeronautics and Astronautics, 2004, 30(09): 855-858. (in Chinese)

Optimal design of composite sandwich structure

  • Received Date: 19 Jun 2003
  • Publish Date: 30 Sep 2004
  • The aeroelastic property of a wing can be improved by using the bending-twisting coupling effect of composite material skin. A genetic algorithm approach was employed to optimize this type structure in order to maximize the effect of bending twisting coupling and a sandwich structure to be an analysis example. A finite element software was used to analysis the objective function, the strength of the sandwich structure were used as the restriction function. The genetic algorithms optimum and finite element analysis function were integrated so that a structure optimal software was developed for complex structure optimization.

     

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  • [1] Kodiyalam S, Nagendra S. Composite sandwich structure optimization with application to satellite components[J]. AIAA Journal, 1996, 34(3):614~621 [2] 中国航空研究院. 复合材料设计手册[M]. 北京:航空工业出版社,2001 Chinese Institute of Aeronautics. Design manual for composite [M]. Beijing:Aviation Industry Press, 2001(in Chinese) [3] 崔德刚. 结构稳定性设计手册[M]. 北京:航空工业出版社, 1996 Cui Degang. Design manual for structural stability[M]. Beijing:Aviation Industry Press,1996(in Chinese) [4] Malott B, Averill R C, Goodman E D. Use of genetic algorithms for optimal design of laminated composite sandwich panels with bending –twisting coupling . AIAA-96-1538-CP, 1996. 1874~1879 [5]Liu Boyang. Composite wing structure optimization using genetic algorithms and response surfaces . AIAA-98-4854, 1998.1~12
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