北京航空航天大学学报 ›› 1999, Vol. 25 ›› Issue (5): 543-545.

• 论文 • 上一篇    下一篇

进气道进口几何参数模糊优化设计

李敬1, 李天2, 武哲1   

  1. 1. 北京航空航天大学 飞行器设计与应用力学系;
    2. 沈阳飞机研究所
  • 收稿日期:1998-04-13 出版日期:1999-05-31 发布日期:2010-11-19
  • 作者简介:男 28岁 博士生 100083 北京

Fuzzy Optimization of the Geometrical Parameters of Fighter Inlet

Li Jing1, Li Tian2, Wu Zhe1   

  1. 1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics;
    2. Shenyang Institute of Aircraft
  • Received:1998-04-13 Online:1999-05-31 Published:2010-11-19

摘要: 重点研究二维两波系超音速外压式两侧/侧腹进气道的进口几何参数的气动力/隐身一体化优化设计,主要考虑进气道的压缩板角、唇口斜切角、罩唇位置角、进口宽度、进口宽高比等进口几何参数所决定的一些气动力性能,如总压恢复系数,超音速溢流附加阻力系数及电磁散射机理如压缩楔板的表面散射、楔板及唇口的边缘绕射,采用基于目标满意度和约束满足度的模糊优化模型,进行了优化计算.

Abstract: For two-dimensional, two-shock, all-external compression, supersonic, cheek-type inlet, the integrated aerodynamic-stealth design of geometrical parameters, such as width, ratio of width and height, angle of vertical compressing ramp, two cutting bevels of the lip plane and lip-position-angle, was investigated by considering those objectives such as the total pressure recovery coefficient, additional drag coefficient of supersonic overflow and the RCS(Radar Cross Section). The formulae for calculating the total pressure recovery coefficient, additional drag coefficient of supersonic overflow were derived. The satisfactory functions of the objectives and the restrictions were given, and then ,based on these functions, the multiobjective fuzzy optimization model was established.

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