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

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-)

	Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method
	Zhu JJ 3; Wang XJ 3; Zhang HG 2; Li YW 2; Wang RX(王睿星)1; Qiu ZP 3
刊名	CHINESE JOURNAL OF AERONAUTICS
	2019-09-01
卷号	32 期号:9 页码:2095-2108
关键词	Hypersonic vehicle Six sigma robust optimization Successive response surface Thermal protection system Uncertainty
ISSN号	1000-9361
DOI	10.1016/j.cja.2019.04.009
通讯作者	Wang, Xiaojun(xjwang@buaa.edu.cn)
英文摘要	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.
分类号	二类/Q1
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]
WOS关键词	RELIABILITY-ANALYSIS ; 6-SIGMA ; BEHAVIORS ; MODELS
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:000492014900006
资助机构	National Key Research and Development Program of China ; National Nature Science Foundation of China ; Defence Industrial Technology Development Programs of China
其他责任者	Wang, Xiaojun
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/81397]
专题	力学研究所_流固耦合系统力学重点实验室(2012-)
作者单位	1.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China 2.704 Res Inst CSIC, Shanghai 200031, Peoples R China; 3.Beihang Univ, Sch Aeronaut Sci & Engn, Inst Solid Mech, Beijing 100083, 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.