超声速巡航导弹轴对称进气道型面优化设计  

Optimization Design of Axisymmetric Inlet of Supersonic Cruising Missile

作　　者：杨铁成[1] 谷良贤[1] 龚春林[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《导弹与航天运载技术》2011年第2期10-14,共5页Missiles and Space Vehicles

摘　　要：针对超声速轴对称式进气道进行型面优化设计。以最大总压恢复系数为目标函数,进行锥体斜激波系的优化设计,迭代计算出超声速段锥体斜激波系的最佳优化配置;按照一维绝热、无粘假设进行超声速混压式进气道的起动设计;在亚声速扩压器优化设计中采用多模块等面积扩压规律,有效地避免喉道后扩张-收缩结构的出现,改善高马赫数下的气流分离特性。这种优化方法可为大空域、宽马赫数工作的超声速进气道设计提供参考。This paper gives optimization design of an axisymmetric supersonic inlet.To achieve the maximum total pressure recovery coefficient,the optimal allocation of a series of supersonic oblique shock waves,passing by a cone configuration,has been calculated using an iterative program.In accordance with the one-dimensional adiabatic,inviscid theory,the start design method of supersonic mixed-compression inlets has been presented.Finally,optimal design of the subsonic diffuser is given with the multi-module equal areas scheme,which is one of the best ways to avoid diverging-converging geometry structure after the throat and could also improve the performance of the flow separation at high Mach number.This optimization method could provide references to the design of supersonic cruising missile＇s inlets with large airspace and wide Mach numbers.

关 键 词：吸气式推进系统 亚燃冲压发动机 超声速进气道 数值模拟 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]