固体火箭技术2026，Vol.49Issue(4)：501-507,7.DOI:10.7673/j.issn.1006-2793.2026.04.002
超音速分离线摆动喷管型面的代理优化方法
Surrogate optimization of supersonic split line nozzle profile
童悦 1李修明 1郑庆1
作者信息
- 1. 上海航天动力技术研究所,上海 201109
- 折叠
摘要
Abstract
To address the aerodynamic shape optimization of supersonic split line(SSSL)nozzle under multiple operation conditions,an efficient surrogate-assisted Bayesian optimization method was established in combination with three-dimensional numerical simulations,and the optimal solution was obtained.The variance-based Sobol sensitivity analysis method was employed to quantify the sensitivity of characteristic variables.The results demonstrate that the performance of the optimized SSSL nozzle is improved by 15.6%,indicating significant overall optimization benefits and validating the effectiveness of the optimization design method for the SSSL nozzle under multiple operating conditions.Partial dependence plot analysis indicates that the initial expansion-section half-angle α,the outlet expansion half-angle β and the downstream arc radius R exhibit weak overall effects on the response.The distance from the swing center to the throat diameter Lr dominates the response,whereas the interaction between the half-angle of the initial expansion section(α)and the expansion ratio at the split line(ε2)is strong.关键词
超音速分离线/摆动喷管/扩张比/代理模型/型面优化Key words
supersonic split line nozzle/swing nozzle/expansion ratio/surrogate model/profile optimization分类
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童悦,李修明,郑庆..超音速分离线摆动喷管型面的代理优化方法[J].固体火箭技术,2026,49(4):501-507,7.
