火箭推进2025，Vol.51Issue(6)：53-66,14.DOI:10.3969/j.issn.1672-9374.2025.06.006
宽域双通道可调喷管高速通道优化设计
Optimized design of high-speed channel for wide-range dual-channel adjustable nozzle
摘要
Abstract
To address the high-speed channel profile design problem of dual-channel adjustable nozzle under the conflict of strong geometric constraints and wide-range performance,parameter-sensitive analysis and multi-objective optimization were combined to reveal the nonlinear regulation mechanism of the design parameters,and a multi-objective optimization strategy was proposed to achieve the synergistic optimization of thrust and lift at the design point and non-design points.The numerical results show that the height of the upper expansion surface has a dominant effect on the wide-area performance,and its positive effect at the design point accounts for 45％,while its negative effect at the non-design point is as high as 80％,and its nonlinear effect accounts for 8％-12％.Appropriate reduction of the upper expansion surface height,exit half-angle and elliptic half-length axis,while increasing the elliptic half-short half-axis and transition arc radius can improve the nozzle's wide-area performance.The thrust coefficient of the optimized high-speed channel is always above 0.955.Compared with the pre-optimization,its design point lift coefficient is improved by 4.25％,the thrust is decreased by only 2.04％,and the thrust coefficient of the non-design point is significantly improved by 7.30％.关键词
TBCC/喷管设计/宽域/双通道/多目标优化设计Key words
TBCC/nozzle design/wide-range/dual-channel/multi-objective optimization design分类
航空航天引用本文复制引用
杨学良,李永洲,袁熠祺,孙迪,刘起立..宽域双通道可调喷管高速通道优化设计[J].火箭推进,2025,51(6):53-66,14.基金项目
国家重点实验室基金(6142701210102,SY41F202412062) （6142701210102,SY41F202412062）
江西省双千计划创新领军人才项目(CK202206068) （CK202206068）
航空科学基金(20240012056001). （20240012056001）
