高超声速二维进气道多目标优化

Multi-objective Optimization Design of Two-dimensional Hypersonic Inlet

从方案论证角度,对高超声速进气道的多目标优化问题进行了分析,对马赫数6的单点工作的进气道提出了以总压恢复系数和进气道喉道马赫数为优化目标,以流量系数为约束条件,对马赫数4.5－6工作的进气道提出了以马赫数6状态的总压恢复系数和喉道马赫数为优化目标,以马赫数6状态的流量系数、马赫数4.5状态的流量系数以及马赫数4.5状态的喉道马赫数为约束条件。同时,给出了一种二维进气道参数化方法和性能计算方法。在此基础上,采用遗传算法进行优化,获得了二维进气道的多目标优化结果,结果表明采用本文方法对高超声速二维进气道进行优化设计是切实可行的。

Based on the scheme design demand of hypersonic inlet, the optimization objectives and constraint conditions were proposed for inlet within single flight Mach number 6 and inlet within a range of flight Mach number 4.5 - 6. To the single flight Mach number optimization problem, the objective functions are the total pressure recovery coefficient and the Mach number of the throat, the constraint condition is the mass flow rate. To a range of flight Mach number optimization problem, the objective functions are the total pressure recovery coefficient and the Mach number of the throat at Ma = 6 condition, the constraint conditions are the mass flow rate at Ma = 6 and Ma = 4.5, and the Mach number of the throat at Ma = 4.5. At the same time, parametric design method and performance calculation method were established. Finally, two cases of multi-objective optimization on two-dimensional hypersonic inlet were simulated. The results show that this method is feasible.