Parameter optimization of dual gas flow combined thermal test based on surrogate model

被引：0

作者：

Rong A. ^{[1
]}

Qi B. ^{[1
]}

Chen X. ^{[2
]}

Wang R. ^{[3
]}

Dong S. ^{[3
]}

Zhou Y. ^{[1
]}

机构：

[1] Qian Xuesen Laboratory of Space Technology, China Academy of Space Technology, Beijing

[2] Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing

[3] School of Aeronautics Science and Engineering, Beihang University, Beijing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 09期

关键词：

high temperature gas flow; optimization design; surrogate model; thermal test; tip wedge structure;

D O I：

10.13224/j.cnki.jasp.20210658

中图分类号：

学科分类号：

摘要：

In order to ensure the coincidence between heat flux on the surface of the specimen during the dual gas flow combined thermal test and hypersonic aerodynamic heat flow，the test parameters were optimized. Numerical model of the dual gas flow combined heating for typical tip wedge structure was built， 128 samples were selected via the Latin Hypercube sampling method and the adding-point strategy based on fuzzy clustering， and numerical simulation was carried out. Then， Kriging surrogate model and elitist non-dominated sorting generic algorithm were applied in multi-objective optimization，which aimed at minimizing the difference between gas flow heating and hypersonic aerodynamic heating. The results showed that the error of surrogate model was significantly reduced by increasing samples. The maximum of mean relative errors of surface heat flux of 8 test samples was about 7%，and less than 5% in most areas，while the mean value of root mean square errors and the peak value of maximum errors were 1.72% and 13.6%，respectively，indicating that the Kriging surrogate model had high prediction accuracy. What’s more，through optimization，the distribution of surface heat flux by gas flow heating was in good agreement with that of hypersonic aerodynamic heat flow. The relative error of heat flux at stagnation was less than 1%，and no more than 10% at the flat plate area，which showed the effectiveness of parameters optimization of dual gas flow combined thermal test based on Kriging surrogate model. © 2023 BUAA Press. All rights reserved.

引用

页码：2097 / 2106

页数：9

共 19 条

[1]

JOYCE P, GRINDLE L., The hyper-X launch vehicle: challenges and design considerations for hypersonic flight testing, (2005)

[2]

RONDEAU C M, JORRIS T R., X-51A scramjet demonstrator program: waverider ground and flight test[R], Armed Services Technical Information Agency Documents, (2013)

[3]

GRANT P, SUSAN P., A heating analysis of the nosecap and leading edges of the X-34 vehicle, (1998)

[4]

PRABHU D，, LOOMIS M，, VENKATAPATHY E，, Et al., X-33 aerothermal environment simulations and aerothermodynamic design, (1998)

[5]

YAO Feng, DONG Sujun, WANG Jun, Numerical analysis of subsonic high-temperature-gas thermal environment simulation, Journal of Aerospace Power, 25, 4, pp. 768-773, (2010)

[6]

DONG Sujun, QI Bin, LI Zhijie, Et al., Approach and facility for aerodynamic thermal test by lower speed and high-temperature gas flow, Journal of Aerospace Power, 27, 5, pp. 961-968, (2012)

[7]

DONG Sujun, LI Zhijie, WANG Jun, Combined heating method of low speed and high/middle temperature gas flow for thermal test of tip wedge structure, Journal of Aerospace Power, 28, 2, pp. 290-296, (2013)

[8]

CHEN Xin, LIU Li, YUE Zhenjiang, A reduced order modeling for aerothermodynamic of hypersonic vehicles based on surrogate method, Transactions of Beijing Institute of Technology, 36, 4, pp. 340-347, (2016)

[9]

YANG Li, TONG Cao, CHEN Chuang, Et al., Vibration reduction optimization of gear modification based on Kriging model and genetic algorithm, Journal of Aerospace Power, 32, 6, pp. 1412-1418, (2017)

[10]

XIA Lu, WANG Dan, ZHANG Yang, Et al., Aerodynamic optimization method based on adaptive surrogate model, Acta Aerodynamica Sinica, 34, 4, pp. 433-440, (2016)

← 1 2 →