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 JJ1; Wang XJ1; Zhang HG2; Li YW2; Wang RX(王睿星)3; Qiu ZP1
Corresponding AuthorWang, Xiaojun(xjwang@buaa.edu.cn)
Source PublicationCHINESE JOURNAL OF AERONAUTICS
2019-09-01
Volume32Issue:9Pages:2095-2108
ISSN1000-9361
AbstractLightweight 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.
KeywordHypersonic vehicle Six sigma robust optimization Successive response surface Thermal protection system Uncertainty
DOI10.1016/j.cja.2019.04.009
Indexed BySCI ; EI ; CSCD
Language英语
WOS IDWOS:000492014900006
WOS KeywordRELIABILITY-ANALYSIS ; 6-SIGMA ; BEHAVIORS ; MODELS
WOS Research AreaEngineering
WOS SubjectEngineering, Aerospace
Funding ProjectNational 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]
Funding OrganizationNational Key Research and Development Program of China ; National Nature Science Foundation of China ; Defence Industrial Technology Development Programs of China
Classification二类/Q1
Ranking5
ContributorWang, Xiaojun
Citation statistics
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/81398
Collection流固耦合系统力学重点实验室
Affiliation1.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
Recommended Citation
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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