摘要：Constructing metamodel with global high-fidelity in design space is significant in engineering design. In this paper, a double-stage metamodel （DSM） which integrates advantages of both interpolation metamodel and regression metamodel is constructed. It takes regression model as the first stage to fit overall distribution of the original model, and then interpolation model of regression model approximation error is used as the second stage to improve accuracy. Under the same conditions and with the same samples, DSM expresses higher fidelity and represents physical characteristics of original model better. Besides, in order to validate DSM characteristics, three examples including Ackley function, airfoil aerodynamic analysis and wing aerodynamic analysis are investigated, In the end, airfoil and wing aerodynamic design optimizations using genetic algorithm are presented to verify the engineering applicability of DSM.

摘要：为解决硼基贫氧燃料固体火箭超燃冲压发动机补燃室内硼颗粒超声速点火燃烧难题,设计制造了在超声速燃气射流掺混区域开设观察窗的点火燃烧过程试验样机,开展了含硼贫氧固体燃料的超声速点火试验。试验模拟了26 km,Ma5.9的飞行工况并通过高速摄像获得了点火燃烧过程的火焰形态。试验结果表明:掺混增强装置可以显著改善补燃室内存在的分层流动和一次燃气气固两相分离的现象,为硼颗粒提供良好的点火条件从而提升其附近硼颗粒的点火燃烧性能。通过合理设计掺混增强装置位置,将硼颗粒在一次燃气喷注口附近的高温点火区点燃比在补燃室中段点燃具有更高的燃烧效率,本文设计的燃烧组织结构在试验中实现了硼贫氧固体燃料0.812的燃烧效率。

摘要：侵蚀燃烧对无喷管助推器的性能有着至关重要的影响。为了在无喷管助推器设计中准确预测其性能,在分析侵蚀燃烧机理的基础上,利用一维非定常变截面内弹道计算程序,采用几种典型的侵蚀燃烧模型对单燃速锥柱形装药和双燃速串装锥柱形装药发动机的特性进行分析。研究表明,文中推进剂在单燃速锥形装药发动机中表现出较弱的负侵蚀效应,采用无负侵蚀效应的侵蚀燃烧模型的预示结果好于带有负侵蚀效应的侵蚀模型,其中Lenoir-Robillard模型的预示精度最高。而双燃速串装发动机中由于燃气流速较小的范围更大,负侵蚀效应影响较大,只有使用具有负侵蚀效应的Greatrix模型才能得到较为准确的预示结果。