Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method
文献类型：期刊论文
| 作者 | Zhu JJ3; Wang XJ3; Zhang HG2; Li YW2; Wang RX(王睿星)1; Qiu ZP3 |
| 刊名 | CHINESE JOURNAL OF AERONAUTICS
 |
| 出版日期 | 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 |
| WOS关键词 | RELIABILITY-ANALYSIS ; 6-SIGMA ; BEHAVIORS ; MODELS |
| 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 |
| 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. |
入库方式： OAI收割
来源：力学研究所
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