弹用二元混压超声速进气道设计与试验研究
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摘要
固体火箭冲压发动机以其良好的性能和巨大的潜在应用优势为世界航空和航天所瞩目，而超声速进气道是其关键部件之一，开展相关研究具有重要的理论意义和工程应用价值。
文中论述了弹用进气道的发展和国内外研究现状，分析了超声速进气道的特点，分别研究了二维和三维混压式超声速进气道的设计方法，采用等激波强度法对唇口楔角混压式进气道进行了设计，并对设计点和非设计点流场进行了数值模拟，通过对数值模拟结果的分析，确定了性能最优的进气道型面方案和进气道布局方案；在理论分析基础上，设计了进气道1／3缩比模型，对缩比模型进行了吹风试验。结合数值模拟和风洞试验的结果，对进气道流场特征进行了研究。
进行了多方案二元混压超声速进气道设计和筛选，确定了主设计方案，并完成试验研究。实验结果表明，按该设计理论设计的进气道在一定马赫数、攻角和侧滑角范围内具有良好的工作性能，满足了设计要求，研究中采用的一维波系设计、二维仿真选择进气道型面、三维仿真确定进气道布置方案、通过模型风洞吹风试验验证的技术路线是高效、合理、可行的。
Due to the good performance and potential appliance dominance of the solid rocket ramjet,the attention of many countries focuses on the study of the solid rocket ramjet. Consequently the study of supersonic inlet is significant in theory and engineering application.
This thesis introduces the development of the solid rocket ramjet technology domestically and abroad. Characteristics of supersonic inlet are analyzed in this paper. The design methods of two-dimensional and three-dimensional mixed compression supersonic inlet and isolater are studied. The two-dimensional mixed compression supersonic inlet with wedge lip is designed by using the method of equal shock wave intensity. The software was employed to simulate the flow field of the design and off-design conditions. The optimal scheme was determined by adjusting the model size of two-dimensional inlet and the distribution of inlet. On the basic of theory analysis, a 1/3 scale model of a 2-D mixed-compression supersonic intake was tested. the two-dimensional mixed compression supersonic inlet has been studied experimentally and numerically.
Through many schemes design and filter of 2-D mixed-compression supersonic intake, confirm the design scheme of experimental investation. The experimental results show that according as this design method, to a certainty range of mach number, attack angle and sideslip angle, intake has favorable capability. In the process of study, it is a supernal efficiency and reasonable and feasible technical route to designed by one-dimensional wave series theory and confirmed the model size of inlet by two-dimensional numerical simulation and confirmed the distribution of inlet by the three-dimensinal numerical simulation and tested by wind tunnel test of reduced scale model.
文中论述了弹用进气道的发展和国内外研究现状，分析了超声速进气道的特点，分别研究了二维和三维混压式超声速进气道的设计方法，采用等激波强度法对唇口楔角混压式进气道进行了设计，并对设计点和非设计点流场进行了数值模拟，通过对数值模拟结果的分析，确定了性能最优的进气道型面方案和进气道布局方案；在理论分析基础上，设计了进气道1／3缩比模型，对缩比模型进行了吹风试验。结合数值模拟和风洞试验的结果，对进气道流场特征进行了研究。
进行了多方案二元混压超声速进气道设计和筛选，确定了主设计方案，并完成试验研究。实验结果表明，按该设计理论设计的进气道在一定马赫数、攻角和侧滑角范围内具有良好的工作性能，满足了设计要求，研究中采用的一维波系设计、二维仿真选择进气道型面、三维仿真确定进气道布置方案、通过模型风洞吹风试验验证的技术路线是高效、合理、可行的。
Due to the good performance and potential appliance dominance of the solid rocket ramjet,the attention of many countries focuses on the study of the solid rocket ramjet. Consequently the study of supersonic inlet is significant in theory and engineering application.
This thesis introduces the development of the solid rocket ramjet technology domestically and abroad. Characteristics of supersonic inlet are analyzed in this paper. The design methods of two-dimensional and three-dimensional mixed compression supersonic inlet and isolater are studied. The two-dimensional mixed compression supersonic inlet with wedge lip is designed by using the method of equal shock wave intensity. The software was employed to simulate the flow field of the design and off-design conditions. The optimal scheme was determined by adjusting the model size of two-dimensional inlet and the distribution of inlet. On the basic of theory analysis, a 1/3 scale model of a 2-D mixed-compression supersonic intake was tested. the two-dimensional mixed compression supersonic inlet has been studied experimentally and numerically.
Through many schemes design and filter of 2-D mixed-compression supersonic intake, confirm the design scheme of experimental investation. The experimental results show that according as this design method, to a certainty range of mach number, attack angle and sideslip angle, intake has favorable capability. In the process of study, it is a supernal efficiency and reasonable and feasible technical route to designed by one-dimensional wave series theory and confirmed the model size of inlet by two-dimensional numerical simulation and confirmed the distribution of inlet by the three-dimensinal numerical simulation and tested by wind tunnel test of reduced scale model.
引文
[1] 冲压发动机在远距空空导弹上的应用前景．航空兵器，1998(1)
[2] A Sfockenstrom, M Morelli. Development of a Supersonic Inlet Capability for Integral Rocket Ramjet Applicationgs. ISABE, 95-7 120: 1308～1314
[3] 刘兴洲，张传民等．飞航导弹动力装置(上)[M]．北京：宇航出版社，1992，1
[4] 赵鹤书，潘杰元等，飞机进气道气动原理，北京：国防工业出版社，1989
[5] 航天器与导弹用冲压／火箭冲压发动机推进系统，推进技术，1989．7
[6] 陈再新．空气动力学．北京：国防工业出版社，1993
[7] 李存杰，龙玉珍．整体式冲压发动机的几项关键技术问题．飞航导弹，1992，3：46—49
[8] Bendot J G，战术导弹用冲压发动机进气系统的设计
[9] 戴国栋，二元外压式侧面进气道气动设计及性能计算。航天部科技报告
[10] 郭荣伟，刘少永．埋入式进气道的设计，南京航空航天大学学报，2001，33(1)：8-12
[11] RAMAKRISHNAN S V, GOLDBERG U C, OTA D K. Numerical computation of hypersonic turbulent flows using zero-and one-equation models[R]. AIAA 89-2234-CP
[12] ASLAN A R, GRUNDMANN R. Accurate prediction of three dimensional intake flow[R]. ISABE 91-7075, 712-723.
[13] Willoh R G. Mathmatic Analysis of Supersonic Inlet Dynamics, NASA TND-4969, 1968
[14] NG W F, AJMANI K, TAYLOR A C. Turbulence modeling in hypersonic irdet[R]. AIAA 88-2957.
[15] RAMAKRISHNAN S V, GOLDBERG U C, OTAD K. Numerical computation of hypersonic turbulent flows using zero-and-one-equation models[R]. AIAA 89-2234-CE
[16] LARS-ERIK ERIKSSON.Navier-Stokes simulations applied to air inlet configured for ramjet powered missiles[R]. ISABE 91-7076, 724-730
[17] A. Ristori and E. Dufor. Numerical simulation of ducted rocket motor[J]. AIAA 2001-3193, 2001.
[18] DUVEAU P, P. TEPOT R. Prediction methods for supersonic inlets[R]. ISABE 91-7078, 738-745
[19] GAIBLE F, GARNERO P, KEGHIAN S. CFD for scramjet inlets[A]. Second European symposium on Aerothermodynamics for spaceehicles [C] November, 1994, 557-563.
[20] TINDELL R H, HILL W G. CFD analysis of the X-29 inlet at high angle of attack [R]. ISABE 91-7074, 703-711
[21] 郑日恒．冲压发动机技术的发展动向与评议．飞航导弹，2004(1)
[22] 曹军伟等．空空导弹动力装置现状与展望．中国宇航学会固体火箭推进专业委员会2001年年会论文集
[23] 王志吉，罗振兵，胡建新．国外固体火箭冲压发动机的研制现状和发展趋势．湖北航天科技，2002(5)
[24] R Marguet. Ramjet Research and Applications in France. ISABE 89-7005
[25] Developments in Missile Ramjet Propulsion. AD-A322627
[26] Three Nations Sigh Meteor Go—ahead. Jane Missile & Rocket, 2001/8
[27] Meteor. Missile Forecast. Dec. 2002
[28] Meteor(BVRAAM). Word Missile Briefing, June 2000
[29] 邓隆范，李国雄，成楚之．二元混压式超声速进气道性能预估及优化设计．现代防御技术，2002(10)Rocket，2001／8
[30] 李博，梁德旺．混压式进气道与弹体一体化流场数值模拟[J]．推进技术，2002，23(4)：307—310
[31] 王国辉，李进贤，蔡体敏．空—空导弹用二元混压超声速进气道数值研究．推进技术，2000，21(4)
[32] 崔金平，徐东来，蔡选义，弹用二元混压超音速进气道设计与仿真．航空兵器，2002(3)
[33] 薛桂林，王健．整体式冲压发动机试验研究，推进技术，1998
[34] 马铁犹，韩振学．超音进气道流场的数值模拟[R]．航空航天工业部，中国国防科技报告GF 83133
[35][35] 张玉伦，陈作斌，程玲，朱国林，刘刚．前可机身—进气道内外流场数值模拟[R]．中国国防科技报告 GF 83139
[36] 董松野．弹用亚、跨音S型进气道研究的一些进展[J]．推进技术，1988．9
[37] 陈大光，张津．飞机—发动机性能匹配与优化．北京：北京航空航天大学出版社，1990
[38] 郑小清，沈慧俐．大迎角下前机身一进气道内外流场数值模拟[R]．中国国防科技报告，GF-A0011018G1991
[39] 谢文超，徐东来，蔡选义．空空导弹推进系统设计．国防工业出版社，2006．(7)
[40] 鲍福廷等．固冲发动机双下侧二元进气道设计研究，西北工业大学学报，2002．11
[41] Goldsmith E L. Some Aspects and Airframe Integration for Ramiet and Ramrocet Powered Missile[R]. NASA N85-15812
[42] Mahoney J John. Inlets for Supersonic Missle[M]. AIAA Education Series, 1990
[43] YEE H C, WARMING R F, HARTEN A. Implicit total variation diminishing (TVD) schemes for steady-state ca/culations[J]. JCP 1985, 57: 327-360
[44] Spa/art p, Allmaras S. A one-equation turbulence model for aero- dynamic flows[R]. AIAA-92-0439
[45] Verstee H K, Malalasekera W. An introduction to computational fluid dynamics: the finite volume methods[M]. Beijing World Publishing CorporAtion, 2000
[46] Lacau R G, Gamero P, Gaible F. Computaton of Supersonic Air-intake[R]. ADA295492
[47] Thompson J F, Warsi Z U A, Mastin C W. Numberrical grid generation: foundations and application[M]. North-Holland, 1985
[48] 严恒元．飞行器气动特性分析与工程计算，西北工业大学出版社，1990．6
[49] 郭应均．超音速进气道流场和附面层计算．中国气动力研究与发展中心
[50] 马铁犹，韩振学．超音进气道流场的数值模拟[R]．航空航天工业部，中国国防科技报告GF 83133
[51] 林超强．进气道网格生成的一种方法。西北工业大学学报，1993，11(2)
[2] A Sfockenstrom, M Morelli. Development of a Supersonic Inlet Capability for Integral Rocket Ramjet Applicationgs. ISABE, 95-7 120: 1308～1314
[3] 刘兴洲，张传民等．飞航导弹动力装置(上)[M]．北京：宇航出版社，1992，1
[4] 赵鹤书，潘杰元等，飞机进气道气动原理，北京：国防工业出版社，1989
[5] 航天器与导弹用冲压／火箭冲压发动机推进系统，推进技术，1989．7
[6] 陈再新．空气动力学．北京：国防工业出版社，1993
[7] 李存杰，龙玉珍．整体式冲压发动机的几项关键技术问题．飞航导弹，1992，3：46—49
[8] Bendot J G，战术导弹用冲压发动机进气系统的设计
[9] 戴国栋，二元外压式侧面进气道气动设计及性能计算。航天部科技报告
[10] 郭荣伟，刘少永．埋入式进气道的设计，南京航空航天大学学报，2001，33(1)：8-12
[11] RAMAKRISHNAN S V, GOLDBERG U C, OTA D K. Numerical computation of hypersonic turbulent flows using zero-and one-equation models[R]. AIAA 89-2234-CP
[12] ASLAN A R, GRUNDMANN R. Accurate prediction of three dimensional intake flow[R]. ISABE 91-7075, 712-723.
[13] Willoh R G. Mathmatic Analysis of Supersonic Inlet Dynamics, NASA TND-4969, 1968
[14] NG W F, AJMANI K, TAYLOR A C. Turbulence modeling in hypersonic irdet[R]. AIAA 88-2957.
[15] RAMAKRISHNAN S V, GOLDBERG U C, OTAD K. Numerical computation of hypersonic turbulent flows using zero-and-one-equation models[R]. AIAA 89-2234-CE
[16] LARS-ERIK ERIKSSON.Navier-Stokes simulations applied to air inlet configured for ramjet powered missiles[R]. ISABE 91-7076, 724-730
[17] A. Ristori and E. Dufor. Numerical simulation of ducted rocket motor[J]. AIAA 2001-3193, 2001.
[18] DUVEAU P, P. TEPOT R. Prediction methods for supersonic inlets[R]. ISABE 91-7078, 738-745
[19] GAIBLE F, GARNERO P, KEGHIAN S. CFD for scramjet inlets[A]. Second European symposium on Aerothermodynamics for spaceehicles [C] November, 1994, 557-563.
[20] TINDELL R H, HILL W G. CFD analysis of the X-29 inlet at high angle of attack [R]. ISABE 91-7074, 703-711
[21] 郑日恒．冲压发动机技术的发展动向与评议．飞航导弹，2004(1)
[22] 曹军伟等．空空导弹动力装置现状与展望．中国宇航学会固体火箭推进专业委员会2001年年会论文集
[23] 王志吉，罗振兵，胡建新．国外固体火箭冲压发动机的研制现状和发展趋势．湖北航天科技，2002(5)
[24] R Marguet. Ramjet Research and Applications in France. ISABE 89-7005
[25] Developments in Missile Ramjet Propulsion. AD-A322627
[26] Three Nations Sigh Meteor Go—ahead. Jane Missile & Rocket, 2001/8
[27] Meteor. Missile Forecast. Dec. 2002
[28] Meteor(BVRAAM). Word Missile Briefing, June 2000
[29] 邓隆范，李国雄，成楚之．二元混压式超声速进气道性能预估及优化设计．现代防御技术，2002(10)Rocket，2001／8
[30] 李博，梁德旺．混压式进气道与弹体一体化流场数值模拟[J]．推进技术，2002，23(4)：307—310
[31] 王国辉，李进贤，蔡体敏．空—空导弹用二元混压超声速进气道数值研究．推进技术，2000，21(4)
[32] 崔金平，徐东来，蔡选义，弹用二元混压超音速进气道设计与仿真．航空兵器，2002(3)
[33] 薛桂林，王健．整体式冲压发动机试验研究，推进技术，1998
[34] 马铁犹，韩振学．超音进气道流场的数值模拟[R]．航空航天工业部，中国国防科技报告GF 83133
[35][35] 张玉伦，陈作斌，程玲，朱国林，刘刚．前可机身—进气道内外流场数值模拟[R]．中国国防科技报告 GF 83139
[36] 董松野．弹用亚、跨音S型进气道研究的一些进展[J]．推进技术，1988．9
[37] 陈大光，张津．飞机—发动机性能匹配与优化．北京：北京航空航天大学出版社，1990
[38] 郑小清，沈慧俐．大迎角下前机身一进气道内外流场数值模拟[R]．中国国防科技报告，GF-A0011018G1991
[39] 谢文超，徐东来，蔡选义．空空导弹推进系统设计．国防工业出版社，2006．(7)
[40] 鲍福廷等．固冲发动机双下侧二元进气道设计研究，西北工业大学学报，2002．11
[41] Goldsmith E L. Some Aspects and Airframe Integration for Ramiet and Ramrocet Powered Missile[R]. NASA N85-15812
[42] Mahoney J John. Inlets for Supersonic Missle[M]. AIAA Education Series, 1990
[43] YEE H C, WARMING R F, HARTEN A. Implicit total variation diminishing (TVD) schemes for steady-state ca/culations[J]. JCP 1985, 57: 327-360
[44] Spa/art p, Allmaras S. A one-equation turbulence model for aero- dynamic flows[R]. AIAA-92-0439
[45] Verstee H K, Malalasekera W. An introduction to computational fluid dynamics: the finite volume methods[M]. Beijing World Publishing CorporAtion, 2000
[46] Lacau R G, Gamero P, Gaible F. Computaton of Supersonic Air-intake[R]. ADA295492
[47] Thompson J F, Warsi Z U A, Mastin C W. Numberrical grid generation: foundations and application[M]. North-Holland, 1985
[48] 严恒元．飞行器气动特性分析与工程计算，西北工业大学出版社，1990．6
[49] 郭应均．超音速进气道流场和附面层计算．中国气动力研究与发展中心
[50] 马铁犹，韩振学．超音进气道流场的数值模拟[R]．航空航天工业部，中国国防科技报告GF 83133
[51] 林超强．进气道网格生成的一种方法。西北工业大学学报，1993，11(2)