| 高超声速二维进气道参数化设计方法初探 |
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| 引用本文： | 范晓樯,李桦,李晓宇,丁国昊.高超声速二维进气道参数化设计方法初探[J].航空动力学报,2007,22(1):66-72. |
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| 作者姓名： | 范晓樯 李桦 李晓宇 丁国昊 |
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| 作者单位： | 国防科学技术大学,航天与材料工程学院,湖南,长沙,410073 |
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| 摘 要： | 通过高超声速二维进气道流动与几何参数制约关系分析和参数敏感性分析,确定了能够对二维进气道进行参数化设计的5个基本几何控制参数,初步建立了高超声速二维进气道的参数化设计方法.结果表明该方法选择的基本参数能够敏感地反映进气道的关键性能和尺寸,为二维进气道型面优化设计提供了切实可行的途径.
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| 关 键 词： | 航空、航天推进系统 高超声速 进气道 优化设计 参数化设计 高超声速 进气道 参数化 型面优化设计 方法初探 inlet hypersonic method of parametric design 尺寸 性能 参数敏感性分析 方法选择 结果 设计方法 控制参数 几何参数 制约关系 流动 |
| 文章编号： | 1000-8055(2007)01-0066-07 |
| 收稿时间： | 2005/12/23 0:00:00 |
| 修稿时间： | 2005年12月23 |
Preliminary investigation on parametric design method of thetwo dimensional hypersonic inlet |
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| FAN Xiao-qiang,LI Hu,LI Xiao-yu and DING Guo-hao.Preliminary investigation on parametric design method of thetwo dimensional hypersonic inlet[J].Journal of Aerospace Power,2007,22(1):66-72. |
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| Authors: | FAN Xiao-qiang LI Hu LI Xiao-yu and DING Guo-hao |
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| Institution: | College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China;College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China;College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China;College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China |
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| Abstract: | A parametric design method of the two-dimensional hypersonic inlet was established.By analyzing the restriction and sensitivity of the parameters which affect the inlet performance or configuration,five basic geometric parameters were selected for the parametric inlet design.It is indicated that the key performance and the configuration of the inlet are sensitive to the basic parameters selected.The parametric design method provides a practical way for the optimization design of the two-dimensional inlet. |
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| Keywords: | aerospace propulsion system hypersonic inlet optimization design parametric design |
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