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。
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.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1999年第5期543-545,共3页
Journal of Beijing University of Aeronautics and Astronautics
关键词
进气道
多目标规划
模糊规划论
一体化设计
air inlets
multiple objective programming
fuzzy programming theory
integrated aerodynamic stealth design
