进口轴向和水平投影同时可控的内收缩进气道设计

李永洲; 孙迪; 张堃元; 郭世亮

doi:10.13224/j.cnki.jasp.2018.04.010

进口轴向和水平投影同时可控的内收缩进气道设计

doi: 10.13224/j.cnki.jasp.2018.04.010

1.
中国航天科技集团有限公司西安航天动力研究所,西安 710100；中国航天科技集团有限公司航天系统发展研究中心,北京 100094
2.
中国航天科技集团有限公司航天系统发展研究中心,北京 100094
3.
南京航空航天大学能源与动力学院,南京 210016

基金项目: 国家自然科学基金（90916029，11702205）

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出版历程
- 收稿日期: 2016-10-26
- 刊出日期: 2018-04-28

Design of inward turning inlet with simultaneous control of intake axial and horizontal projections

摘要

摘要: 为了满足两侧进气布局高超声速飞行器乘波前体与进气道一体化设计要求,基于特征线法和流线追踪技术提出了一种进口轴向投影和水平投影同时可控的内收缩进气道设计方法。采用该方法设计了进口轴向投影和水平投影均为超椭圆的内收缩进气道并在设计点(马赫数为6.0）对其进行数值仿真验证。结果表明：进气道进口轴向投影和水平投影均符合预期设计。进气道能保持基准流场的波系结构和沿程压力分布,无黏时可以全捕获来流,喉道截面性能与基准流场基本相等。有黏时,进气道也具有较高的压缩效率,流量系数和出口总压恢复系数分别为0.96和0.56。因此，上述设计方法可行有效。
- 内收缩进气道 /
- 反设计 /
- 投影形状 /
- 流线追踪 /
- 特征线法
Abstract: Based on the rotational method of characteristics and streamline tracing technique, the design method was developed for inward turning inlet with control of the axial and horizontal projections of intake, so as to meet the integrated design requirements of hypersonic vehicle waverider forebody and inlet with both sides intake layout. The inward turning inlet was designed utilizing this design method for the axial and horizontal projections of intake of super ellipse. Numerical simulation was conducted at design point Mach number of 6.0. The results indicate that the axial and horizontal projections of intake conform to the anticipated design. The inlet can retain the wave structure and pressure distribution of basic flowfield, and capture all of free incoming flow under the inviscid condition. Its performance of throat plane is almost equal to basic flowfield. Under the viscous condition, the inlet has high compression efficiency; the flow coefficient and total pressure recovery coefficient of exit plane are 0.96 and 0.56, respectively. This design method is feasible and effective.
- inward turning inlet /
- inverse design /
- projection shape /
- streamline tracing /
- method of characteristics

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参考文献(25)

[1]	王磊,张堃元,金志光,等.基于壁面压力分布的二元高超声速弯曲激波压缩进气道反设计与优化方法［J］.推进技术,2013,34(12):1601-1605.WANG Lei,ZHANG Kuyuan,JIN Zhiguang,et al.Reverse design and optimization of 2D hypersonic curved shock compression inlet based on given wall pressure distribution［J］.Journal of Propulsion Technology,2013,34(12):1601-1605.(in Chinese)
[2]	高文智,李祝飞,杨基明.一种鼻锥钝化高超声速轴对称进气道流动特性实验［J］.航空学报,2015,36(1)：302-310.GAO Weizhi,LI Zhufei,YANG Jiming.Flow characteristics experiments of a hypersonic axisymmetric inlet with nose bluntness［J］.Acta Aeronautica et Astronautica Sinica,2015,36(1):302-310.(in Chinese)
[3]	ZHANG Lin,ZHANG Kunyuan,WANG Lei.Experimental study of three-dimensional sidewall compression inlet designed on wall Mach number linear distribution curved surface compression system［R］.AIAA-2015-3669,2015.
[4]	BILLIG F S,JACOBSEN L S.Comparison of planar and axisymmetric flow paths for hydrogen fueled space access vehicle［R］.AIAA-2003-4407,2003.
[5]	YOU Yancheng.An overview of the advantages and concerns of hypersonic inward turning inlets［R］.AIAA-2011-2269,2011.
[6]	朱呈祥,黄国平,尤延铖,等.内乘波式进气道与典型侧压式进气道的性能对比［J］.推进技术,2011,32(2):151-158.ZHU Chengxiang,HUANG Guoping,YOU Yancheng,et al.Performance comparison between internal waverider inlet and typical sidewall compression inlet［J］.Journal of Propulsion Technology,2011,32(2):151-158.(in Chinese)
[7]	BULMAN M J,SIEBENHAAR A.The rebirth of round hypersonic propulsion［R］.AIAA-2006-5035,2006.
[8]	ZHANG Kunyuan.Research progress of hypersonic inlet inverse design based on curved shock compression system［R］.AIAA-2015-3647,2015.
[9]	BILLIG F S,KOTHARI A.Streamline tracing:technique for designing hypersonic vehicles［J］.Journal of Propulsion and Power,2000,16(3):465-471.
[10]	OTTO S E,TREFNY C J,SLATER J W.Inward turning streamline-traced inlet design method for low-boom,low-drag applications［R］.AIAA-2015-3700,2015.
[11]	尤延铖,梁德旺.基于内乘波概念的三维变截面高超声速进气道［J］.中国科学E辑：技术科学,2009,39(8):1483-1494.YOU Yancheng,LIANG Dewang.Design concept of three dimensional section controllable internalwaverider hypersonic inlet［J］.Science in China Series E:Technological Sciences,2009,39(8):1483-1494.(in Chinese)
[12]	SMART M K.Design of three-dimensional hypersonic inlets with rectangular-to-elliptical shape transition［J］.Journal of Power and Propulsion,1999,15(3):408-416.
[13]	郭军亮,黄国平,尤延铖,等.改善内乘波式进气道出口均匀性的内收缩基本流场研究［J］.宇航学报,2009,30(5):1934-1940.GUO Junliang,HUANG Guoping,YOU Yancheng,et al.Study of internal compression flow field for improving the outflow uniformity of internal wave rider inlet［J］.Journal of Astronautics,2009,30(5):1934-1940.(in Chinese)
[14]	SABEAN J W,LEWIS M J.Computational optimization of a hypersonic rectangular-to-circular inlet［J］.Journal of Propulsion and Power,2001,17(3):571-578.
[15]	MATTHEWS A J,JONES T V.Design and test of a modular waverider hypersonic intake［J］.Journal of Propulsion and Power,2006,22(4):913-920.
[16]	NAN Xiangjun,ZHANG Kunyuan.Numerical and experimental investigation on hypersonic inward turning inlets with basic flow field using arc tangent curve law of pressure rise［R］.AIAA-2011-2270,2011.
[17]	李永洲,张堃元,孙迪.马赫数可控的方转圆高超声速内收缩进气道实验研究［J］.航空学报,2016,37(10):2970-2979.LI Yongzho,ZHANG Kunyuan,SUN Di.Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape transition with controlled Mach number distribution［J］.Acta Aeronautica et Astronamtica Sinica,2016,37(10):2970-2979.(in Chinese)
[18]	李永洲,张堃元,朱伟,等.双弯曲入射激波的可控中心体内收缩基准流场设计［J］.航空动力学报,2015,30(3):563-570.LI Yongzhou,ZHANG Kunyuan,ZHU Wei,et al.Design for inward turning basic flowfield withbody and two incident curved shock controlled center waves［J］.Journal of Aerospace Power,2015,30(3):563-570.(in Chinese)
[19]	WALKER S H,TANG M,MORRIS S,et al.Falcon HTV-3X-a reusable hypersonic test bed［R］.AIAA-2008-2544,2008.
[20]	SIEBENHAAR A,BOGAR T J.Integration and vehicle performance assessment of the aerojet “trijet” combined-cycle engine［R］.AIAA-2009-7420,2009.
[21]	南向军,张堃元,金志光.乘波前体两侧高超声速内收缩进气道一体化设计［J］.航空学报,2012,33（8）:1417-1426.NAN Xanjun,ZHANG Kunyuan,JIN Zhiguang.Integrated design of waverider forebody and lateral hypersonic inward turning inlets［J］.Acta Aeronautica et Astronautica Sinica,2012,33(8):1417-1426.(in Chinese)
[22]	李永洲,张堃元,孙迪,等.进口型线水平投影可控的变截面内收缩进气道设计［J］.航空学报,2017,38(5):115-123.LI Yongzho,ZHANG Kunyuan,SUN Di,et al.Design on variable section inward turning inlet with controlled horizontal projection of in-take curve［J］.Acta Aeronautica et Astronautica Sinica,2017,38(5):115-123.(in Chinese)
[23]	钱翼稷.超音速轴对称有旋流特征线法的计算程序［J］.北京航空航天大学报,1996,22(4):454-459.QIAN Yiji.Computer program of supersonic axisymmetric rotational characteristic method［J］.Journal of Beijing University of Aeronautics and Astronautics,1996,22(4):454-459.(in Chinese)
[24]	乔文友,黄国平,夏晨,等.发展用于高速飞行器前体/进气道匹配设计的逆特征线法［J］.航空动力学报,2014,29(6):1444-1452.QIAO Wenyou,HUANG Guoping,XIA Chen,et al.Development of inverse characteristic method for matching design of high-speed aircraft forebody/inlet［J］.Journal of Aerospace Power,2014,29(6):1444-1452.(in Chinese)
[25]	DRAYNA T W,NOMPELIS I,CANDLER G V.Hypersonic inward turning inlets:design and optimization［R］.AIAA-2006-297,2006.