Multi-objective optimization design of hypersonic axisymmetric inlet

被引：0

作者：

Wang C. ^{[1
]}

Eriqitai ^{[1
]}

Ding W. ^{[1
]}

机构：

[1] School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2020年 / 35卷 / 07期

关键词：

Axisymmetric inlet; Multi-objective optimization design; NSGA-Ⅱ; algorithm; Parametric design; Surrogate model;

D O I：

10.13224/j.cnki.jasp.2020.07.007

中图分类号：

O29 [应用数学];

学科分类号：

070104 ;

摘要：

Taking the hypersonic axisymmetric inlet as the research object, firstly, parametric design of the inlet profile was carried out, and seven parameters, such as the general conic saturation, the general conic control line, the transition arc radius, the throat corner, the throat straight line to height ratio, the center line control parameter and the equivalent cone angle, were selected as the design variables to carry out the multi-objective design of the inlet. In the design process, the initial sample points were determined by orthogonal test design method, and Kriging surrogate models between two optimization objectives of inlet total pressure recovery coefficient and outlet distortion with design parameters were established. The surrogate model was analyzed and solved by the second generation of Non-Dominated Sorting Genetic Algorithm (NSGA-Ⅱ). The results showed that after multi-objective optimization, the total pressure recovery performance of the inlet increased by 2.63%, and the outlet distortion reduced by 27.57%. © 2020, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：1392 / 1401

页数：9

共 21 条

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