火箭推进2026，Vol.52Issue(2)：1-12,12.DOI:10.3969/j.issn.1672-9374.2026.02.001
二元内并联进气道高速通道优化设计
Optimized design of high-speed channel in a two-dimensional internal parallel inlet
摘要
Abstract
To enhance the wide Mach number performance of the high-speed channel in a two-dimensional internal parallel inlet,a multi-point and multi-objective optimization design method based on fully parameterized flow-path modeling was proposed.An integrated parametric model of the external and internal compression sections was first developed,thereby revealing the nonlinear response and strong coupling mechanism between the performance of the high-speed channel and the design parameters.On this basis,the Kriging surrogate model and the NSGA-Ⅱ algorithm were combined to collaboratively optimize the performance at both the design point(6.0Ma)and the off-design point(4.0Ma).The optimized configuration exhibits significant performance improvements across the wide-speed range.Compared with a conventional three-wedge inlet,the optimized inlet achieves a 6.4％increase in total pressure recovery at the design condition(6.0Ma),and at the off-design condition(4.0Ma),the mass-flow coefficient and total pressure recovery coefficient are enhanced by 9.8％and 4.8％,respectively.The"modeling-analysis-optimization"integrated design framework developed in this study effectively addresses the issues inherent in traditional hypersonic inlet design,such as insufficient coupling between the external and internal compression sections and the difficulty in achieving balanced performance across a wide Mach number range.关键词
高超声速进气道/内并联进气道/参数化建模/多目标优化/宽速域性能Key words
hypersonic inlet/internal parallel inlet/fully parametric modeling/multi-objective optimization/wide-range performance分类
航空航天引用本文复制引用
李洲,李永洲,孙迪,刘晶,李欢,胡杰华..二元内并联进气道高速通道优化设计[J].火箭推进,2026,52(2):1-12,12.基金项目
江西省双千计划创新领军人才项目(CK202206068) （CK202206068）
国家重点实验室基金(6142701210102) （6142701210102）
航空科学基金(20240012056001). （20240012056001）
