高超声速二维进气道参数化设计方法初探

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

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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出版历程
- 收稿日期: 2005-12-23
- 修回日期: 2006-06-09
- 刊出日期: 2007-01-28

Preliminary investigation on parametric design method of thetwo dimensional hypersonic inlet

College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China

摘要

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.
- 航空、航天推进系统 /
- 高超声速 /
- 进气道 /
- 优化设计 /
- 参数化设计
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.
- aerospace propulsion system /
- hypersonic /
- inlet /
- optimization design /
- parametric design

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参考文献(17)

[1]	Van Wie D M,Molder S.Applications of busemann inlet designs for flight at hypersonic speeds[R].AIAA Paper 92-1210.1992.
[2]	Smart M K.Design of three-dimensional hypersonic inlets with rectangular to elliptical shape transition[R].AIAA Paper 98-0960.1998.
[3]	ANDERSON W E,WONG N D.A two-dimensional mixed-compression inlet system designed to self-restart at a Mach number of 3.5[J].Journal of Aircraft,1970,7(5):431-436.
[4]	Falempin F,Goldfeld M.Design and experimental evaluation of a Mach 2-Mach 8Inlet.[R].AIAA Paper 2001-1890.2001.
[5]	Coratekin T,Van Keuk J,Ballmann J.Preliminary investigations in 2D and 3D ramjet inlet design[R].AIAA Paper 99-2667.1999.
[6]	黎明,宋文艳,贺伟.高超声速二维混压式前体/进气道设计方法研究[J].航空动力学报,2004,19(4):459-465.LI Ming,SONG Wenyan,HE Wei.Design method of two-dimensional hypersonic forebody/Inlet of mixed compression[J].Journal of Aerospace Power,2004,19(4):459-465.
[7]	YANTA W J,COLLIER A S,SPRING W C,et al.Experimental measurements of the flow in a scramjet inlet at Mach 4[J].Journal of Propulsion and Power,1990,6(6):784-790.
[8]	Shukla V,Gelsey A,Schwabacher M,et al.Automated design optimization for the P2 and P8 hypersonic inlets[J].Journal of Aircraft,1997,34(2):228-235.
[9]	Auneau I.Design and optimazation methods for scrarnjet Inlets[R].AIAA Paper 95-6017.1995.
[10]	徐旭,蔡国彪.超燃冲压发动机二维进气道优化设计方法研究[J].推进技术,2001,22(6):468-472.XU Xu,CAI Guobiao.Design and optimization method for two dimensional scramjet inlet[J].Journal of Propulsion Technology,2001,22(6):468-472.
[11]	施磊,董金钟.二维高超声速进气道设计优化[J].航空发动机,2004,30(4):18-21.SHI Lei,DONG Jinzhong.Design optimization of two-dimensional hypersonic Inlet[J].Aeroengine,2004,30(4):18-21.
[12]	宋道军,胥继斌.高超声速二维前体进气道一体化优化设计研究[J].空气动力学学报,2004,22(3):371-375.SONG Daojun,XU Jibin.Optimal integrated design of two-dimensional hypersonic vehicle's forebodys and inlets[J].Acta Aerodynamica Sinica,2004,22(3):371-375.
[13]	Smart M K.Optimazation of two-dimensional scramjet inlets[J].Jorunal of Aircraft,1999,36(2):430-433.
[14]	罗世彬,罗文彩,丁猛,等.超燃冲压发动机二维进气道多级多目标优化设计方法[J].国防科技大学学报,2004,26(3):1-6.LUO Shibin,LUO Wencai,DING Meng,et al.The multi-level and multiobjective optimization design method for two dimensional scramjet inlet[J].Journal of National University of Defense Technology,2004,26(3):1-6.
[15]	Chernyavsky B,Stepanov V.3-D Hypersonic inlet optimization using a genetic algorithm[R].AIAA Paper 98-3582.1998.
[16]	Matthews A J,Jones T V.Design and test of a low-drag hypersonic intake[R].AIAA Paper 2003-7045.2003.
[17]	余安远,乐嘉陵.一种高超声速轴对称导弹用进气道的前体-喉道的设计与数值模拟[R].2005冲压发动机技术交流会,吉林,2005.