北京航空航天大学学报 ›› 2015, Vol. 41 ›› Issue (9): 1659-1665.doi: 10.13700/j.bh.1001-5965.2014.0641

• 论文 • 上一篇    下一篇

三角形机翼参数化有限元网格划分与调整方法

许孟辉, 邱志平   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2014-10-16 出版日期:2015-09-20 发布日期:2015-09-29
  • 通讯作者: 邱志平(1962—),男,吉林长春人,教授,zpiu@buaa.edu.cn, 主要研究方向为飞行器设计、结构动力学、可靠性分析与优化设计等. E-mail:zpiu@buaa.edu.cn
  • 作者简介:许孟辉(1986—),男,山东德州人,博士研究生,13716408732@163.com
  • 基金资助:
    北京航空航天大学博士研究生创新基金(YWF-14-YJSY-017); 国防基础科研项目(JCKY2013601B)

Parametric finite element meshing and adjustment for delta wing

XU Menghui, QIU Zhiping   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2014-10-16 Online:2015-09-20 Published:2015-09-29

摘要: 为缩短有限元建模周期,提高三角形机翼结构分析、设计与优化的效率疲,首先,以其满足预定气动性能的几何外形为输入,定义了易用的有限元节点与单元的编号规则;基于可设计的机翼内部构型参数及可变的有限元尺寸参数的设置,引入了翼肋贯穿截止准则以满足任意输入的内部构型的初步判断;借助自定义形状矩阵完成了节点布置与单元生成,进一步通过有限元网格细化完成了开口设置、翼肋贯穿位置修正及桁条建模.然后,基于已建立的有限元网格实现了内外侧副翼翼肋位置的小幅调整及旋转舵面的角度调整,以满足不同飞行状态下结构分析需求.最后,应用PCL语言开发了参数化建模模块,实例表明了方法的有效性和模块可靠性.

关键词: 三角形机翼, 参数化建模, 有限元模型, PCL语言, 二次开发

Abstract: 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.

Key words: delta wing, parametric modeling, finite element model, Patran command language (PCL) language, redevelopment

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