高超声速二维前体进气道一体化优化设计研究  

Optimal integrated design of two-dimensional hypersonic vehicle's forebodies and inlets

作　　者：宋道军[1] 胥继斌[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2004年第3期371-375,共5页Acta Aerodynamica Sinica

摘　　要：在飞行器前体进气道的一体化优化设计中,最大总压恢复系数是一个必须考虑的参数。本文从二维高超声速进气道的最大总压恢复系数入手,通过理论分析给出了高超声速飞行器从2波系到6波系的二维高超声速飞行器前体进气道的一体化优化设计计算模型。采用拉格朗日乘子法和序列二次规划法(SQP)分别计算了进气道内一道内激波和两道内激波时的情况,给出了进气道的最大总压恢复系数、进气道内马赫数、激波偏转角和激波强度随来流马赫数的变化关系。比较两种方法的计算结果可知采用的计算方法是合理的。The maximum total pressure recovery is an important factor in optimal integrated design of two-dimensional scramjet inlet. In present paper, in order to get the maximum total pressure recovery of two-dimensional hypersonic vehicle inlets, a computational model with up to six shocks are presented. Both Lagrange multipliers method and sequence quadratic programming method are used independently to solve the problem with one and two internal shocks. Despite this, the interrelation of maximum total pressure recovery and inlet Mach number and shock turning angles and the shock strengths with freestream Mach number are all presented.

关 键 词：高超声速进气道 总压恢复系数 高超声速飞行器 来流马赫数 激波 二维 SQP 变化关系 偏转角 序列二次规划法 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V231.3