| 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 Author | Wang, Xiaojun([email protected]) |
| Source Publication | CHINESE JOURNAL OF AERONAUTICS
 |
| 2019-09-01 | |
| Volume | 32Issue:9Pages:2095-2108 |
| ISSN | 1000-9361 |
| Abstract | 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. |
| Keyword | Hypersonic vehicle Six sigma robust optimization Successive response surface Thermal protection system Uncertainty |
| DOI | 10.1016/j.cja.2019.04.009 |
| Indexed By | SCI ; EI ; CSCD |
| Language | 英语 |
| WOS ID | WOS:000492014900006 |
| WOS Keyword | RELIABILITY-ANALYSIS ; 6-SIGMA ; BEHAVIORS ; MODELS |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | 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] |
| Funding Organization | National Key Research and Development Program of China ; National Nature Science Foundation of China ; Defence Industrial Technology Development Programs of China |
| Classification | 二类/Q1 |
| Ranking | 5 |
| Contributor | Wang, Xiaojun |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/81398 |
| Collection | 流固耦合系统力学重点实验室 |
| Affiliation | 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 |
| 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.Rp_Au:Wang, Xiaojun |
| 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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| Jp2019528.pdf（2082KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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