Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method

doi:10.1016/j.cja.2019.04.009

IMECH-IR > 流固耦合系统力学重点实验室

	Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method
	Zhu JJ 1; Wang XJ 1; Zhang HG 2; Li YW 2; Wang RX(王睿星)3; Qiu ZP 1
通讯作者	Wang, Xiaojun(xjwang@buaa.edu.cn)
发表期刊	CHINESE JOURNAL OF AERONAUTICS
	2019-09-01
卷号	32 期号:9 页码:2095-2108
ISSN	1000-9361
摘要	Lightweight design is important for the Thermal Protection System (TPS) of hypersonic vehicles in that it protects the inner structure from severe heating environment. However, due to the existence of uncertainties in material properties and geometry, it is imperative to incorporate uncertainty analysis into the design optimization to obtain reliable results. In this paper, a six sigma robust design optimization based on Successive Response Surface Method (SRSM) is established for the TPS to improve the reliability and robustness with considering the uncertainties. The uncertain parameters related to material properties and thicknesses of insulation layers are considered and characterized by random variables following normal distributions. By employing SRSM, the values of objective function and constraints are approximated by the response surfaces to reduce computational cost. The optimization is an iterative process with response surfaces updating to find the true optimal solution. The optimization of the nose cone of hypersonic vehicle cabin is provided as an example to illustrate the feasibility and effectiveness of the proposed method. (C) 2019 Chinese Society of Aeronautics and Astrona Lilies. Production and hosting by Elsevier Ltd.
关键词	Hypersonic vehicle Six sigma robust optimization Successive response surface Thermal protection system Uncertainty
DOI	10.1016/j.cja.2019.04.009
收录类别	SCI ; EI ; CSCD
语种	英语
WOS记录号	WOS:000492014900006
关键词[WOS]	RELIABILITY-ANALYSIS ; 6-SIGMA ; BEHAVIORS ; MODELS
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
资助项目	National Key Research and Development Program of China[2016YFB0200700] ; National Nature Science Foundation of China[11872089] ; National Nature Science Foundation of China[11572024] ; National Nature Science Foundation of China[11432002] ; Defence Industrial Technology Development Programs of China[JCKY2016601B001] ; Defence Industrial Technology Development Programs of China[JCKY2016204B101] ; Defence Industrial Technology Development Programs of China[JCKY2017601B001]
项目资助者	National Key Research and Development Program of China ; National Nature Science Foundation of China ; Defence Industrial Technology Development Programs of China
论文分区	二类/Q1
力学所作者排名	5
RpAuthor	Wang, Xiaojun
引用统计	被引频次：18[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/81398
专题	流固耦合系统力学重点实验室
作者单位	1.Beihang Univ, Sch Aeronaut Sci & Engn, Inst Solid Mech, Beijing 100083, Peoples R China; 2.704 Res Inst CSIC, Shanghai 200031, Peoples R China; 3.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Zhu JJ,Wang XJ,Zhang HG,et al. Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method[J]. CHINESE JOURNAL OF AERONAUTICS,2019,32,9,:2095-2108.
APA	Zhu JJ,Wang XJ,Zhang HG,Li YW,王睿星,&Qiu ZP.(2019).Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method.CHINESE JOURNAL OF AERONAUTICS,32(9),2095-2108.
MLA	Zhu JJ,et al."Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method".CHINESE JOURNAL OF AERONAUTICS 32.9(2019):2095-2108.

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