Comparison of Strategies for Coupled Flow-Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition

doi:10.1007/s42405-019-00217-x

CORC > 力学研究所 > 中国科学院力学研究所 > 流固耦合系统力学重点实验室(2012-)

	Comparison of Strategies for Coupled Flow-Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition
	Wang RX(王睿星)2,3; Wang, ZW 1; Zheng HW(郑洪伟)3,4; Song HW(宋宏伟)2,3
刊名	INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES
	2020-06-01
卷号	21 期号:2 页码:347-362
关键词	Coupled flow-thermal analysis Thermal protection system Basic direct correction method (BDCM) Improved DCM (IDCM) Iteration solution method (ISM)
ISSN号	2093-274X
DOI	10.1007/s42405-019-00217-x
通讯作者	Wang, Ruixing(wangruixing@imech.ac.cn)
英文摘要	Coupled flow-thermal analysis is crucial for the performance evaluation and structural design of hypersonic vehicles. In this study, several strategies for computing the coupled flow-thermal response of air-breathing hypersonic flights in practical engineering are developed and compared. First, the basic direct correction method that amends wall heat flux via recovery temperature and wall temperature is proposed to approximate flow-thermal effects efficiently. Second, the improved DCM (IDCM) is further developed by interpolating the cold wall heat flux and the recovery temperature between adjacent trajectory points to improve computational accuracy. Third, the iteration solution method (ISM) that obtains solutions through mass and energy balances at a common interface by iterations between CFD analysis code and CSD analysis code is also presented. Thermal response and flow characteristics are compared through a test case of an air-breathing hypersonic vehicle. The results show that the thermal response tendencies are consistent by DCMs and ISM. However, for DCMs, the impact of hot wall on the flow characteristics is ignored, whereas it is fully considered in ISM; thus, the thickened boundary flow and complicated internal flow can be captured. However, while comparing computational efficiency, DCMs have a prominent advantage over ISM due to the decoupling algorithm and parallel strategy. Based on this, in the actual design process of an air-breathing hypersonic vehicle, the designers can select the proper flow-thermal analysis method according to the different design stages.
分类号	Q4
WOS关键词	ABLATION
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:000535454100005
其他责任者	Wang, Ruixing
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/82078]
专题	力学研究所_流固耦合系统力学重点实验室(2012-) 力学研究所_高温气体动力学国家重点实验室
作者单位	1.China Acad Launch Vehicle Technol, Ctr Res & Dev, Beijing 100076, Peoples R China; 2.Chinese Acad Sci, Inst Mech, Key Lab Mech Fluid Solid Coupling Syst, Beijing 100190, Peoples R China; 3.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China; 4.Chinese Acad Sci, Inst Mech, Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Wang RX,Wang, ZW,Zheng HW,et al. Comparison of Strategies for Coupled Flow-Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition[J]. INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES,2020,21(2):347-362.
APA	王睿星,Wang, ZW,郑洪伟,&宋宏伟.(2020).Comparison of Strategies for Coupled Flow-Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition.INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES,21(2),347-362.
MLA	王睿星,et al."Comparison of Strategies for Coupled Flow-Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition".INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES 21.2(2020):347-362.