北京航空航天大学学报 ›› 2014, Vol. 40 ›› Issue (12): 1666-1671.doi: 10.13700/j.bh.1001-5965.2014.0015

• 论文 • 上一篇    下一篇

基于多点约束的大展弦比机翼静气动弹性计算

黄炜, 陆志良, 唐迪, 郭同庆   

  1. 南京航空航天大学 航空宇航学院, 南京 210016
  • 收稿日期:2014-01-14 出版日期:2014-12-20 发布日期:2014-12-30
  • 作者简介:黄 炜(1965-),男,河南临颖人,博士生,huangwei@comac.cc.
  • 基金资助:

    国家自然科学基金资助项目(11372135);江苏高校优势学科建设工程资助项目

MPC based static aeroelastic numerical method for high aspect ratio wing

Huang Wei, Lu Zhiliang, Tang Di, Guo Tongqing   

  1. Colleg of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2014-01-14 Online:2014-12-20 Published:2014-12-30

摘要:

基于雷诺平均N-S方程和多块结构网格技术计算大展弦比机翼的气动力.机翼采用梁模型结构,利用有限元方法计算结构变形.建立基于多点约束(MPC,Multi-Point Constrain)的气动、结构数据的双向传递方法.采用MPC数据插值方法快捷地实现自主研发的计算流体力学(CFD,Computational Fluid Dynamics)程序和NASTRAN计算结构力学(CSD,Computational Structural Dynamics)软件的耦合计算,发展出可以考虑结构非线性的静气动弹性CFD/CSD耦合计算方法,该方法比只考虑单方向变形的柔度法更精确.开展了某大展弦比机翼的静气动弹性数值计算分析,结果显示只考虑机翼纵向变形而忽略展向变形对计算结果会有一定影响,而该算例几何非线性影响较小.

关键词: 大展弦比机翼, 有限元方法, N-S方程, 静气动弹性, 多块结构网格

Abstract:

The steady aerodynamic loads were calculated with N-S equations and the multi-block structured grid technique was used to improve the computational efficiency. A beam model was applied to a high aspect ratio wing, and its structural deformations were evaluated by the finite element method with or without geometry nonlinearity. A multi-point constrain (MPC) method was used for the information exchange between the aerodynamic loads calculations and the structure deformations calculations. The static aeroelasticity was further considered. By successive iterations between self-developed computational fluid dynamics (CFD) solver and NASTRAN computational structural dynamics (CSD) software based on the MPC interpolation method, a quick and accurate coupled CFD-CSD method was achieved for the nonlinear static aeroelastic problem. Obviously the present method is more accurate than the conventional flexibility approach only considering single-direction deformation. Numerical analysis of a high aspect ratio wing demonstrates that spanwise deformation would have certain influence on its static aeroelastic characteristics and that geometric nonlinearity has small effect on this common airliner wing.

Key words: high aspect ratio wing, finite element method, N-S equations, static aeroelasticity, multi-block structured grid

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