Volume 41 Issue 9
Sep.  2015
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XU Menghui, QIU Zhiping. Parametric finite element meshing and adjustment for delta wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1659-1665. doi: 10.13700/j.bh.1001-5965.2014.0641(in Chinese)
Citation: XU Menghui, QIU Zhiping. Parametric finite element meshing and adjustment for delta wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1659-1665. doi: 10.13700/j.bh.1001-5965.2014.0641(in Chinese)

Parametric finite element meshing and adjustment for delta wing

doi: 10.13700/j.bh.1001-5965.2014.0641
  • Received Date: 16 Oct 2014
  • Publish Date: 20 Sep 2015
  • To reduce the time of finite element (FE) modeling for a delta wing as well as improve the efficiency of structural analysis, design and optimization, a method, with the only input of its geometry profile meeting the pre-defined aerodynamic performance, for parametric modeling based on the self-defined geometrical matrix was established. Number rules for nodes and elements were firstly defined. And preliminary identification of the inner skeleton configuration with respect to arbitrary input parameters was subsequently accomplished by the criteria for rib-end locations. Nodes and elements were then generated by user-input parameters for the finite element size. Secondly the FE meshing was refined by the opening setting, amendment of rib-end locations and stringers modeling, based on which modifications of rib assignment with small amplitude for both the inside and outside ailerons as well as those of the rotation angle for control surfaces were made for ease in use of structural analysis under different flying conditions. At last, a parametric modeling module was simultaneously programmed using Patran command language (PCL) language and examples illustrate the effectiveness and reliability of the proposed method.

     

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