Shape parameters optimization of hypersonic vehicle based on surrogate model

被引：0
|
作者：
Yi C. [1 ]
Liu Y. [1 ]
Cao R. [2 ]
Tang J. [2 ]
Zhu H. [2 ]
He J. [1 ]
机构：
[1] College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] College of Automation, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2019年 / 34卷 / 11期
关键词：
Gap metric; Hypersonic vehicle; Model comparison; Shape parameters optimization; Surrogate model;
D O I：
10.13224/j.cnki.jasp.2019.11.007
中图分类号：
学科分类号：
摘要：
In view of the complexity and difficulty of hypersonic vehicle analysis, a surrogate model was proposed to approximate the true model with complex disciplinary coupling in the process of performance analysis and optimization. According to the requirements of cruise mission, the objective of optimization was to optimize the static and dynamic performance and minimize the model difference. By means of sensitivity analysis, the surrogate model was established. The static and dynamic performance analysis of the surrogate model was carried out, and the results of the true model were compared to verify the accuracy of the surrogate model. It was found that the trend of the trimming characteristics of the two models was completely consistent, the difference of angle of attack was less than 3%, and the difference of elevator deflection angle was only about 20% when the lower angle of the front body was large. Based on the surrogate model and optimized performance index, the trimming performance optimization and gap metric optimization of the surrogate model's shape parameters were compared with the optimization results of the true model and the optimization efficiency. It was found that the difference between the two results was less than 2%, but the optimization efficiency using surrogate model was improved by 456%. It was proved that the optimization based on the surrogate model can improve the optimization efficiency without compromise of the accuracy. © 2019, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2354 / 2365
页数：11
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