冲压增程弹丸进气道流场的实验与数值模拟
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摘要
本文对冲压增程弹丸所用发动机的双锥超声速进气道在各种工况条件下的流场进行了数值模拟，给出了进气道流场的等压线图、等密度线图和等马赫线图，从而观察在不同的锥尖角组合、锥芯与外罩唇口的相对位置、出口反压、来流马赫数和攻角时，对进气道流场及性能参数的影响，并探讨喘振现象的产生机理及诱导因素，以便确定最佳的工作状态，得到最优的进气道模型。通过建立三维结构化网格模型，选择合适的数值格式与湍流模型，对进气道流场进行数值模拟，得到了合理的结果。同时对以上某型号的进气道模型进行了风洞实验，并与数值模拟的结果进行了对比，其误差率在允许的范围之内，这也进一步验证了所用数值模拟方法的可靠性。因此，上述有关方法和结论将为增程弹丸进气道的设计与更深入地研究提供重要的理论依据。
This paper referred to simulating the supersonic double cone inlet' s flow field of ramjet pill assisted range projectiles at a variety of working circumstances, pressure contours, density contours and Mach number contours of inlet' s flow field were given' When cone combination, relative location of cone core and cowl lip, the pressure of outlet, inflow Mach number and angle were changed, flow field and performance parameters of inlet can be affected. Simultaneity, productive mechanism and inducing factors of the inlet surge were also discussed. Then the best working conditions and the best model of inlet were obtained. After inlet model' s three dimensional structural grid was generated, proper numerical scheme and onflow model were choosed, then numerical computation on flow field of inlet was taken, finally the better results were got. At the same, wind-tunnel experimental research about some inlet model was fulfilled. Then, results of wind-tunnel experiment and results of numerical simulation were comparised, error ratio was under permission range, which ulteriorly validated the reliability of numerical simulation method. Therefore, the conclusions and method of this paper can be helpful to design the inlet of improved range's cannonball theoretically and technologically.
This paper referred to simulating the supersonic double cone inlet' s flow field of ramjet pill assisted range projectiles at a variety of working circumstances, pressure contours, density contours and Mach number contours of inlet' s flow field were given' When cone combination, relative location of cone core and cowl lip, the pressure of outlet, inflow Mach number and angle were changed, flow field and performance parameters of inlet can be affected. Simultaneity, productive mechanism and inducing factors of the inlet surge were also discussed. Then the best working conditions and the best model of inlet were obtained. After inlet model' s three dimensional structural grid was generated, proper numerical scheme and onflow model were choosed, then numerical computation on flow field of inlet was taken, finally the better results were got. At the same, wind-tunnel experimental research about some inlet model was fulfilled. Then, results of wind-tunnel experiment and results of numerical simulation were comparised, error ratio was under permission range, which ulteriorly validated the reliability of numerical simulation method. Therefore, the conclusions and method of this paper can be helpful to design the inlet of improved range's cannonball theoretically and technologically.
引文
1 郭美芳，姜辉．国外基地／舰载远程精确打击弹药的方展研究．防空反导与远程弹药技术论文集，中国兵工学会弹药专业委员会第29届年会，四川成都，2001．9：182-196
2 苏维厚，张莉．远程炮弹火箭增程技术探讨．防空反导与远程弹药技术论文集，中国兵工学会弹药专业委员会第29届年会，四川成都，2001．9：214-217
3 张庆书．大口径弹药技术方展方向．防空反导与远程弹药技术论文集，中国兵工学会弹药专业委员会第29届年会，四川成都，2001．9：218-221
4 顾玉萍．冲压增程炮弹进气道工作特性分析与研究．南京理工大学硕士论文，2004
5 张克勤．冲压推进评论．推进技术，Vol 1，No3，1990
6 梁守磐，王树声．冲压发动机展望．推进技术，Vol 1，No1，1986
7 约翰．霍浦金斯大学应用物理实验所编．冲压发动机技术．国防工业出版社，1980
8 周军(译)，龙玉珍(校)．亚燃／超燃冲压发动机研制动向．飞航道弹，No3，1997
9 张炜，朱慧，方丁酉．冲压发动机发展现状及其关键技术．固体火箭技术，Vol21，No3，2004
10 郑日恒．冲压发动机技术的方展动向与评论．推进技术，No1，2004
11 郭健，张为华，杨涛等．固体燃料冲压发动机研究进展．固体火箭技术，Vol26，No2，2003
12 B.C.朱也夫，B.C.马卡伦．冲压和火箭—冲压发动机原理．国防工业出版社，1975．7
13 M.M.蓬达留克，C.M.伊里雅申柯．冲压式喷气发动机．国防工业出版社，1958
14 刘兴洲，张传民．飞航导弹动力装置(上)．宇航出版社，1992
15 Waltrup P J, White M E, Zarlingo F et al. History of U.S. Navy Ramjet, Scramjet, and Mixed-Cycle Propulsion Development. Journal of Propulsion and Power, 2002, 18(1): 14-27
16 Wilson R, Limage C, Hewitt P. The Evolution of Ramjet Missile Propusion in the U.S. and Where we are Headed. AIAA 96-3148
17 R.F.Calzone. Integral Rocket Ramjets. TNO-report, 1994
18 卢贤锋．超声速进气道内外流场计算与数学模型研究．西北工业大学硕士论文，2003
19 马铁犹，韩振学．超音速进气道流场的数值模拟．航空航天工业部中国国防报告，GF 83133
20 李博，梁德旺．混压式进气道与弹体一体化流场数值模拟．推进技术，Vol23，No4，2002
21 郑小清，沈慧俐．大迎角下前机身-进气道组合体的流场计算．中国国防报告，GF-A0011018C．1991
22 白鹏，朱守梅．冲压发动机进气道掺混段与弹体内外流场一体化数值模拟．空气动力学学报，Vol23，No1，2005
23 张玉伦，陈作斌等．前机身-进气道内外流场数值模拟．中国国防报告，GF 83139
24 Lars-erik, Eriksson. Navier-Stokes simulations applied to air inlets configured for ramjet powered missiles. ISABE91-7076
25 Duveau P, Thepot R. Prediction methods for supersonic inlets. ISABE91-7078
26 Ng W F, Ajmanink, raylor A C. Turbulence modeling inhypersonic inlets. AIAA88-2957
27 蔡飞超．超声速战术导弹进气道／弹身气动干扰数值研究．西北工业大学硕士论文，2005．3
28 晁锐．前机身／进气道流场的一体化数值模拟．西北工业大学硕士论文，2002．3
29 王雨培．超然冲压发动机进排气系统设计及流场数值模拟．西北工业大学硕士论文，2004．3
30 Pulliam T H, Chaussee D S. A Diagonal From of an Implicit Approximate Factorization Algorithm. J Comp Phys, 1981, 39: 347-363
31 Chaussee D S, Pulliam T H. Two-Dimensional Ielet Simulation Using a Diagonal Implicit Algorithm. AIAA J, 1981, 19(2)
32 A.D. Gosman, A.M.Y. Ahmed. Measurement and Multidimensional Prediction of Flow in an Axisymmetric Port/Valve Assembly. SAE, 1987: P592～613
33 Chun-On Cheng, Wal K. Cheng, John B. Heywood. Intake Port Phenomena in a Spark-Ignition Engine at Part Load. SAE, 1991: P1839～1851
34 R.D. Reitz. Improvements in 3-D Modeling of Diesel Engine Intake Flow and Combustion. SAE, 1992: P1627～1648
35 Wolf Bauer, John B. Heywood. Flow Characteristic in Intake Port of Spark Ignition Engine Investigated by CFD and Transient Gas Temperature Measurement. SAE, 1996: P2110～2117
36 王保国，刘秋生．三维湍流高速进气道内外流场的高效高分辨率解．空气动力学报，1996，14(2)：168-178
37 刘仪，刘斌．扩压器进气道内流及激波／边界层干扰的数值研究．空气动力学报，1997，15(2)：256-260
38 王国辉．固体火箭冲压发动机进气道流场数值模拟．西北工业大学硕士论文，1999
39 王福军．计算流体动力学分析——CFD软件原理与应用．清华大学出版社，2004．9
40 高树滋，赵润祥，马大为．火炮流体力学数值方法．兵器工业出版社，1995
41 陈雄．高速旋转固体火箭冲压发动机进气道工作过程特性研究．南京理工大学博士论文，2005
42 刘家利．四气门发动机进气道内流动的三维数值模拟．重庆大学硕士论文，2003
43 封建湖．三维进气道系统的数值模拟研究．西北工业大学博士论文，1995
44 A. Jameson, W. Schmidt and F. Turkel. "Numerical Solution of the Euler Equation by Finite Volume Methods Using Runge-Kutta Time Stepping Schemes", AIAA-81-1259, 1981
45 Yee H CK, lopfer G H, Montagne L G. High resolution abock captureing achemes for inviscid and viscous hypersonic flows. NASA TM 100097, 1988
46 Harten A, Osher S. Uniformly high-order accurate nonoscillalory schemes. J Numer Anal, 1987(24): 279-309
47 Shu C W, Osher S. Efficient implementation of essentially non-oscillatory shock capturing scheme Ⅱ.J Comp Phys, 1988, 77: 439-471
48 DEGANI D, SHIFF L S. Computation of turbulent supersonic flows around pointed bodies having crossflow separation. J Comp Phys, 1968(66): 173-196
49 Yee H C. Construction of explicit and implicit symmetric TVD schemes and their applications. J Comp Phys, 1987(68): 151-179
50 Kermani M J. Development and assessment of upwind schemes with application to inviscid and viscous flows on structured meshes. Carleton University, Canada, PH D, 2001
51 Aslan A R, Grundmann R. Accurate prediction of three dimensional intake flow. ISABE91-7075
52 Lee C H, Chu Y H.A New Type Of TVD Schemes for Computations Of High Speed Flows. AIAA 93-2773
53 韩占忠，忠王敬，兰小平．FLUENT流体工程仿真计算实例与应用．北京理工大学出版社，2004
54 是勋刚．湍流．天津大学出版社，1994．3
55 蔡树棠，刘宇陆．湍流理论．上海交通大学出版社，1993
56 张兆顺，崔桂香，许春晓．湍流理论与模拟．清华大学出版社，2005
57 Ramakrishnan S V, Goldberg U C、Ota D K. Numerical computation of hypersonic turbulent flows using zero- and-one-equation models. AIAA89-2234-CP
58 章梓雄，董曾南．粘性流体力学．清华大学出版社，1998
59 陶文铨．计算传热学的近代发展．科学出版社，2000．6
60 张军．含动边界自适应非结构网格的生成与应用．南京理工大学博士论文，2004．10
61 王铁城等．空气动力学实验技术．国防工业出版社，1986．4
62 恽起麟．实验空气动力学．国防工业出版社，1991．12
63 王淑芬(译)，王家明(校)．试验导弹用火箭冲压发动机进气道．飞航道弹，No1，1997
64 薛桂林，王健．四进气道整体式冲压发动机试验研究．推进技术，Vol19，No4，1998
65 F.K.利特尔等．内流空气动力学手册．国防工业出版社(第1册)，1982
2 苏维厚，张莉．远程炮弹火箭增程技术探讨．防空反导与远程弹药技术论文集，中国兵工学会弹药专业委员会第29届年会，四川成都，2001．9：214-217
3 张庆书．大口径弹药技术方展方向．防空反导与远程弹药技术论文集，中国兵工学会弹药专业委员会第29届年会，四川成都，2001．9：218-221
4 顾玉萍．冲压增程炮弹进气道工作特性分析与研究．南京理工大学硕士论文，2004
5 张克勤．冲压推进评论．推进技术，Vol 1，No3，1990
6 梁守磐，王树声．冲压发动机展望．推进技术，Vol 1，No1，1986
7 约翰．霍浦金斯大学应用物理实验所编．冲压发动机技术．国防工业出版社，1980
8 周军(译)，龙玉珍(校)．亚燃／超燃冲压发动机研制动向．飞航道弹，No3，1997
9 张炜，朱慧，方丁酉．冲压发动机发展现状及其关键技术．固体火箭技术，Vol21，No3，2004
10 郑日恒．冲压发动机技术的方展动向与评论．推进技术，No1，2004
11 郭健，张为华，杨涛等．固体燃料冲压发动机研究进展．固体火箭技术，Vol26，No2，2003
12 B.C.朱也夫，B.C.马卡伦．冲压和火箭—冲压发动机原理．国防工业出版社，1975．7
13 M.M.蓬达留克，C.M.伊里雅申柯．冲压式喷气发动机．国防工业出版社，1958
14 刘兴洲，张传民．飞航导弹动力装置(上)．宇航出版社，1992
15 Waltrup P J, White M E, Zarlingo F et al. History of U.S. Navy Ramjet, Scramjet, and Mixed-Cycle Propulsion Development. Journal of Propulsion and Power, 2002, 18(1): 14-27
16 Wilson R, Limage C, Hewitt P. The Evolution of Ramjet Missile Propusion in the U.S. and Where we are Headed. AIAA 96-3148
17 R.F.Calzone. Integral Rocket Ramjets. TNO-report, 1994
18 卢贤锋．超声速进气道内外流场计算与数学模型研究．西北工业大学硕士论文，2003
19 马铁犹，韩振学．超音速进气道流场的数值模拟．航空航天工业部中国国防报告，GF 83133
20 李博，梁德旺．混压式进气道与弹体一体化流场数值模拟．推进技术，Vol23，No4，2002
21 郑小清，沈慧俐．大迎角下前机身-进气道组合体的流场计算．中国国防报告，GF-A0011018C．1991
22 白鹏，朱守梅．冲压发动机进气道掺混段与弹体内外流场一体化数值模拟．空气动力学学报，Vol23，No1，2005
23 张玉伦，陈作斌等．前机身-进气道内外流场数值模拟．中国国防报告，GF 83139
24 Lars-erik, Eriksson. Navier-Stokes simulations applied to air inlets configured for ramjet powered missiles. ISABE91-7076
25 Duveau P, Thepot R. Prediction methods for supersonic inlets. ISABE91-7078
26 Ng W F, Ajmanink, raylor A C. Turbulence modeling inhypersonic inlets. AIAA88-2957
27 蔡飞超．超声速战术导弹进气道／弹身气动干扰数值研究．西北工业大学硕士论文，2005．3
28 晁锐．前机身／进气道流场的一体化数值模拟．西北工业大学硕士论文，2002．3
29 王雨培．超然冲压发动机进排气系统设计及流场数值模拟．西北工业大学硕士论文，2004．3
30 Pulliam T H, Chaussee D S. A Diagonal From of an Implicit Approximate Factorization Algorithm. J Comp Phys, 1981, 39: 347-363
31 Chaussee D S, Pulliam T H. Two-Dimensional Ielet Simulation Using a Diagonal Implicit Algorithm. AIAA J, 1981, 19(2)
32 A.D. Gosman, A.M.Y. Ahmed. Measurement and Multidimensional Prediction of Flow in an Axisymmetric Port/Valve Assembly. SAE, 1987: P592～613
33 Chun-On Cheng, Wal K. Cheng, John B. Heywood. Intake Port Phenomena in a Spark-Ignition Engine at Part Load. SAE, 1991: P1839～1851
34 R.D. Reitz. Improvements in 3-D Modeling of Diesel Engine Intake Flow and Combustion. SAE, 1992: P1627～1648
35 Wolf Bauer, John B. Heywood. Flow Characteristic in Intake Port of Spark Ignition Engine Investigated by CFD and Transient Gas Temperature Measurement. SAE, 1996: P2110～2117
36 王保国，刘秋生．三维湍流高速进气道内外流场的高效高分辨率解．空气动力学报，1996，14(2)：168-178
37 刘仪，刘斌．扩压器进气道内流及激波／边界层干扰的数值研究．空气动力学报，1997，15(2)：256-260
38 王国辉．固体火箭冲压发动机进气道流场数值模拟．西北工业大学硕士论文，1999
39 王福军．计算流体动力学分析——CFD软件原理与应用．清华大学出版社，2004．9
40 高树滋，赵润祥，马大为．火炮流体力学数值方法．兵器工业出版社，1995
41 陈雄．高速旋转固体火箭冲压发动机进气道工作过程特性研究．南京理工大学博士论文，2005
42 刘家利．四气门发动机进气道内流动的三维数值模拟．重庆大学硕士论文，2003
43 封建湖．三维进气道系统的数值模拟研究．西北工业大学博士论文，1995
44 A. Jameson, W. Schmidt and F. Turkel. "Numerical Solution of the Euler Equation by Finite Volume Methods Using Runge-Kutta Time Stepping Schemes", AIAA-81-1259, 1981
45 Yee H CK, lopfer G H, Montagne L G. High resolution abock captureing achemes for inviscid and viscous hypersonic flows. NASA TM 100097, 1988
46 Harten A, Osher S. Uniformly high-order accurate nonoscillalory schemes. J Numer Anal, 1987(24): 279-309
47 Shu C W, Osher S. Efficient implementation of essentially non-oscillatory shock capturing scheme Ⅱ.J Comp Phys, 1988, 77: 439-471
48 DEGANI D, SHIFF L S. Computation of turbulent supersonic flows around pointed bodies having crossflow separation. J Comp Phys, 1968(66): 173-196
49 Yee H C. Construction of explicit and implicit symmetric TVD schemes and their applications. J Comp Phys, 1987(68): 151-179
50 Kermani M J. Development and assessment of upwind schemes with application to inviscid and viscous flows on structured meshes. Carleton University, Canada, PH D, 2001
51 Aslan A R, Grundmann R. Accurate prediction of three dimensional intake flow. ISABE91-7075
52 Lee C H, Chu Y H.A New Type Of TVD Schemes for Computations Of High Speed Flows. AIAA 93-2773
53 韩占忠，忠王敬，兰小平．FLUENT流体工程仿真计算实例与应用．北京理工大学出版社，2004
54 是勋刚．湍流．天津大学出版社，1994．3
55 蔡树棠，刘宇陆．湍流理论．上海交通大学出版社，1993
56 张兆顺，崔桂香，许春晓．湍流理论与模拟．清华大学出版社，2005
57 Ramakrishnan S V, Goldberg U C、Ota D K. Numerical computation of hypersonic turbulent flows using zero- and-one-equation models. AIAA89-2234-CP
58 章梓雄，董曾南．粘性流体力学．清华大学出版社，1998
59 陶文铨．计算传热学的近代发展．科学出版社，2000．6
60 张军．含动边界自适应非结构网格的生成与应用．南京理工大学博士论文，2004．10
61 王铁城等．空气动力学实验技术．国防工业出版社，1986．4
62 恽起麟．实验空气动力学．国防工业出版社，1991．12
63 王淑芬(译)，王家明(校)．试验导弹用火箭冲压发动机进气道．飞航道弹，No1，1997
64 薛桂林，王健．四进气道整体式冲压发动机试验研究．推进技术，Vol19，No4，1998
65 F.K.利特尔等．内流空气动力学手册．国防工业出版社(第1册)，1982