高超声速飞行器/发动机流动控制研究
摘要
本文针对目前流动控制的两种主要方式,即局部加热控制和磁流体控制,分别对高超声速飞行器前体/进气道虚拟前罩流动控制,前体/进气道MHD控制和后体/尾喷管的虚拟舵流动控制进行了数值试验原理验证和局部控制变量的控制特性研究。具体工作如下:
对于飞行器前体/进气道虚拟前罩流动控制,本文在虚拟前罩局部加热控制流场的原理下,确定了虚拟前罩的流动控制计算验证模型,数值计算方法和计算网格结构。通过数值仿真二维的高超声速进气道溢流条件下流场结构和不同控制变量下的性能参数,得到二维的飞行器/前体流动控制性能,说明了主要的控制变量变化对进气道性能的影响。
对于飞行器前体/进气道磁流体流动控制,本文研究了电子束注入形成局部可控等离子体的机制和数学模型,建立了外加磁场对其进行加速减速的计算模型;建立MATLAB与FLUENT的局部计算域数据交换进行耦合求解MHD进气道流场控制的计算平台;通过算例验证了模型的有效性,并计算了在控制位置一定时,能量注入大小的流动控制特性。
对于飞行器后体/尾喷管虚拟舵控制:研究了通过虚拟舵(局部加热)来进行尾喷管推力、升力控制及俯仰力矩控制的有效性。建立了虚拟舵控制的数学模型,二维的计算模型和计算网格结构;通过FLUENT计算在不同的能量注入形状和能量注入大小的情况下,验证虚拟舵提高飞行器/后体尾喷管特性和配平俯仰力矩的有效性,并获得了控制参数的特性。
To improve scramjet propulsion characteristics, this study utilizes two major flow control methods, namely, energy input control and magnetohydrodynamics (MHD) flow control, to control flow flied patterns in such three fields as hypersonic vehicle forebody/inlet virtual cowl flow control, hypersonic vehicle forebody/inlet MHD flow control, and hypersonic vehicle afterbody/nozzle flow control. Numerical computation principles are established and characteristics of control parameters for each application are studied.
First, a virtual cowl control governing equations are explored, for working Mach numbers lower than designed Mach numbers. Computing models, both physical and geometric, are constructed. Validation cases are decided and 2-D computations are executed. Results validate computation methods and accuracy, inlet flow spillage of studied conditions are mitigated, and more importantly inlet performance characteristics are improved. Characteristics for controlling parameters in terms of energy addition amount and heating region locations are presented and analyzed.
Second, for working Mach number higher than designed Mach number, MHD flow control principles are studied. Via analysis on air ionization process and FLUENT governing equations, computing platform of a partial coupling methods are constructed. The platform is based on interaction of data between MATLAB and FLUENT. Computing cases validate the computing platform and indicate that MHD flow control has effective controlling character at non-designed flying condition. Controlling parameter characteristics are also studied.
Finally, a heating region is introduced to scramjet nozzle in order to provide a lift and thrust controlling method. Through establishment of mathematic models and 2-D computing models, validating cases are computed in FLUENT with energy addition via a UDF attachment. Results show that this heating region has effective controlling characteristics.
对于飞行器前体/进气道虚拟前罩流动控制,本文在虚拟前罩局部加热控制流场的原理下,确定了虚拟前罩的流动控制计算验证模型,数值计算方法和计算网格结构。通过数值仿真二维的高超声速进气道溢流条件下流场结构和不同控制变量下的性能参数,得到二维的飞行器/前体流动控制性能,说明了主要的控制变量变化对进气道性能的影响。
对于飞行器前体/进气道磁流体流动控制,本文研究了电子束注入形成局部可控等离子体的机制和数学模型,建立了外加磁场对其进行加速减速的计算模型;建立MATLAB与FLUENT的局部计算域数据交换进行耦合求解MHD进气道流场控制的计算平台;通过算例验证了模型的有效性,并计算了在控制位置一定时,能量注入大小的流动控制特性。
对于飞行器后体/尾喷管虚拟舵控制:研究了通过虚拟舵(局部加热)来进行尾喷管推力、升力控制及俯仰力矩控制的有效性。建立了虚拟舵控制的数学模型,二维的计算模型和计算网格结构;通过FLUENT计算在不同的能量注入形状和能量注入大小的情况下,验证虚拟舵提高飞行器/后体尾喷管特性和配平俯仰力矩的有效性,并获得了控制参数的特性。
To improve scramjet propulsion characteristics, this study utilizes two major flow control methods, namely, energy input control and magnetohydrodynamics (MHD) flow control, to control flow flied patterns in such three fields as hypersonic vehicle forebody/inlet virtual cowl flow control, hypersonic vehicle forebody/inlet MHD flow control, and hypersonic vehicle afterbody/nozzle flow control. Numerical computation principles are established and characteristics of control parameters for each application are studied.
First, a virtual cowl control governing equations are explored, for working Mach numbers lower than designed Mach numbers. Computing models, both physical and geometric, are constructed. Validation cases are decided and 2-D computations are executed. Results validate computation methods and accuracy, inlet flow spillage of studied conditions are mitigated, and more importantly inlet performance characteristics are improved. Characteristics for controlling parameters in terms of energy addition amount and heating region locations are presented and analyzed.
Second, for working Mach number higher than designed Mach number, MHD flow control principles are studied. Via analysis on air ionization process and FLUENT governing equations, computing platform of a partial coupling methods are constructed. The platform is based on interaction of data between MATLAB and FLUENT. Computing cases validate the computing platform and indicate that MHD flow control has effective controlling character at non-designed flying condition. Controlling parameter characteristics are also studied.
Finally, a heating region is introduced to scramjet nozzle in order to provide a lift and thrust controlling method. Through establishment of mathematic models and 2-D computing models, validating cases are computed in FLUENT with energy addition via a UDF attachment. Results show that this heating region has effective controlling characteristics.
引文
1贺武生.超燃冲压发动机研究综述.火箭推进.2005,31(1):30-32
2刘敬华.超燃冲压发动机试验研究的国外动态.推进技术.2002,(3):46-48
3 Macheret,Sergey O., Shneider, Mikhail N., Miles, Richard B. Scramjet inlet control by off-body energy addition: A virtual cowl, AIAA Journal, 42(11): 374
4 H.Yan, D. Gaitonde. Numerical Study on Effect of a Thermal Bump in Supersonic Flow Control.AIAA.39th Plasmadynamic and Lasers Conference, 2008.Seattle USA, AIAA: 1-3
5 Nicholas J. Bisek, Iain D. Boyd. Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles. Journal of Spacecraft and Rockets. 2009, 46(3): 568-568
6 H. Yan, D. Gaitonde, J.S. Shang. Supersonic Flow Control by Pulsed Thermal Bump. 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008. AIAA, 2008: 1-15
7 K.Kontis. Flow Control effectiveness of jets, strakes, and flares at hypersonic speeds. J. of Aerospace Engineering. 222(Special Issue Paper): 585-588
8 Resler RL, Sears WR. The prospects for magneto-aerodynamics. J Aero Sci.. 1958, 25(4):235–45, 258
9 E.M. Braun, F.K.Lu, D.R.Wilson. Experimental research in aerodynamic control with electric and electromagnetic fields. Progress in Aerospace Sciences 2009, 45: 30-49
10 A.L. Kuranov and E.G. Sheikin, Magnetohydrodynamic Control on Hypersonic Aircraft under "AJAX" concept. J Space Rockets. 2003, 40(2):174-182
11 1E.G.Sheikin, A.L.Kuranov. MHD Control in Hypersonic Aircraft. 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reno USA, 2005. AIAA, 2005:1-3
12 A. Kuranov, A.Korabelnikov. Hypersonic technologies of atmospheric Cruise flight Under AJAX concept. 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Dayton, Ohio, USA, 2008.AIAA, 2008:1-5
13 Patrick RM. Magneto-hydrodynamics of compressible fluids. PhD dissertation, Cornell University, Ithaca, NY. 1956: 198
14 Simmons GA, Nelson GL. Overview of the NASA MARIAH project and summary of technical results. AIAA Albuquerque, NM. 1998. 1998-2752: 5-6
15 G. Candler and J. Perkins, Effect of Vibration Nonequilibrium on Axisymmetric Hypersonic Nozzle Design. 29th Aerospace Science Meeting,1991: 1-5
16 Joseph C. Yen, William R. Martindale, An Inviscid Supersonic Nozzle Design Approach to Perfect Flow Uniformity for Wind Tunnel Applications, 26th AIAA Applied Aerodynamics Conference, 2008: 1-3
17 C. Hirchen, P. Gruhn, A. Gülhan, Influence of Heat Capacity Ratio on the Interaction between the External Flow and Nozzle flow of a scramjet, 14th AIAA/AHI Space Planes and Hypersonic System and Technologies Conference, 2006. AIAA, 2006:1-2
18 Palm P, Meyer R, Ploenjes E, Bezant A, Adamovich IV, Rich JW, et al. MHD effect on a supersonic weakly ionized flow. AIAA Maui, HI; May 2002. AIAA, 2002-2246: 3-10
19 Macheret SO, Shneider MN, Miles RB. Modeling of plasma generation in repetitive ultra-short DC, microwave, and laser pulses. Anaheim, CA, USA, 2001. AIAA,2001-2940:5
20吕浩宇,李椿萱,董海涛.三维超声速磁流体发生器的流动特性.中国科学.2009,39(3):435-445
21郭国才.MHD推进的可能性.船电技术, 1995, (02):32
22马丹.提高磁流体推进器电磁效率的一种方法.船电技术.2005, (02): 40
23田正雨,张康平,潘沙,李桦.磁流体动力学斜激波控制数值模拟分析.力学季刊.2008, (01):13
24郑小梅,徐大军,蔡国飙.MHD能量旁路超燃冲压发动机可行性分析.北京航空航天大学学报.2004, (3):12
25潘勇,王江峰,伍贻兆.非结构网格高超声速MHD流场逆风格式数值模拟.宇航学报,2008, 3(01):23
26鲍文,唐井峰,于达仁.MHD-Arc-Ramjet联合循环与AJAX间的性能比较.宇航学报, 2007,(01).
27钟梓鹏,王雨培,宋文艳,邓远灏.超燃冲压发动机尾喷管流场研究.弹箭与制导学报.2005, (SA):27
28 Macheret S.O., Shneider M. N. Miles RB 2001. Phys. Plasmas,2001 (8):1518
29李弘,苏铁,欧阳亮,王慧慧,白小燕,陈志鹏,刘万东.电子束产生大尺度等离子体过程的数值模拟研究.物理学.2006,55(7):7052-7055
30 Chen Li-Hong, Gu HongBin, Zhang Xin-Yu. Experimental study on scramjet with cavity/strut configuration. J. of Engineering Thermophysics. 2007, 28(4):717-719
31张志斌;胡良元;林彬.超燃冲压发动机热防护结构的理论计算.航天制造技术.2008,(4):48-50
32贺元元,乐嘉陵,倪鸿礼.吸气式高超声速机体/推进一体化飞行器数值和试验研究.实验流体力学.2007,21(2):30-33
33韩省思,刘亮,叶桃红,朱旻明,陈义良.三种湍流对Scramjet燃烧室冷态流场的数值模拟.中国科学技术大学学报.2009,39(3):321-324
34肖志祥,符松.用RANSPLES混合方法研究超声速底部流动.计算物理.2009,26(2):223-224
35柳朝晖,贺铸,李瑞霞,郑楚光.各向同性湍流中颗粒引起湍流变动的直接模拟.工程热物理学报.2006.27(1):224
36彭涛,钱若军.大涡模拟(LES)理论研究述评.第八届全国现代结构工程学术研讨会论文集,2008.工业建筑.2008:602-605
37周连第.用两方程模型计算回转体尾部和尾流湍流流动的流线迭代法.力学学报, 1982,(03):226-229
38史峰,徐忠.k-ε两方程模型的改进及其应用.空气动力学学报, 1991,(02):261-263
39王运良,徐忠,苗永淼.使用不同壁面函数对紊流流场计算结果的影响.流体机械, 1993,(12) :26-29
40刘宜,张佳卉.质量出口边界条件在流场模拟中的应用.通用机械, 2005,(06) :81
41 M. N. Shneider, S. O. Macheret, S. H. Zaidi, I. G. Girgis, R. B. Miles. Virtual Shapes in Supersonic Flow Control with Energy Addition. Journal of Propulsion and Power. 2008, 24(5): 900-916
42 VanWie, D. M.,“Scramjet Inlets,”Scramjet Propulsion, edited by E. T. Curran and S. N. B. Murthy, Vol. 189, Progress in Astronautics andAeronautics, AIAA, Reston, VA, 2000, Chap. 7, pp. 447–511.
43 Itikawa, Y., Ichimura, A., Onda, K., Sakimoto, K., Takayanagi, K., Hatano, Y., Hayashi, M., Nashimura, M., Tsurubuchi, S. Cross Sections for Collisions of Electrons and Photons with Oxygen Molecules. J. Phys. Chem. 1989, 18(1):23-42.
44 Itikawa, Y., Hayashi, M., Ichimura, A., Onda, K., Sakimoto, K., Takayanagi, K., Nakamura, M., Takayanagi, T. Cross Sections for Collisions of Electrons and Photons with Nitrogen Molecules. J. Phys. Chem.1986, 15(3): 985-1010
45 Macheret, S.O., Shneider, M.N., and Miles, R.B.Magnetohydrodynamic Control of Hypersonic Flowand Scramjet Inlets Using Electron Beam Ionization.AIAA Journal. 2002, 40,(1): 74-81.
46 Macheret, S.O., Shneider, M.N., Miles, R.B., and Lipinski, R.J. Electron Beam Generated Plasmas in Hypersonic Magnetohydrodynamic Channels. AIAA Journal, 2001, 39(6): 1127-1136
47 Blom, J. H., Hanson, R. K. Double-Discharge Arrangement for CW Electrical Excitation of Supersonic Flows. Applied Physics Letters. 1975, 26(4): 190.
48 M. N. Shneider, Sergey O. Macheret, and Richard B. Miles. Analysis of Magnetohydrodynamic Control of Scramjet Inlets. AIAA Journal. 2004,42(11):2303-2310
49陈兵,徐旭,蔡国飘.二维超燃冲压发动机尾喷管优化设计.推进技术.2002(5):433
50李建平,宋文艳,陈亮.超燃冲压发动机尾喷管性能研究.机械设计与制造, 2008, (02) : 95-97
2刘敬华.超燃冲压发动机试验研究的国外动态.推进技术.2002,(3):46-48
3 Macheret,Sergey O., Shneider, Mikhail N., Miles, Richard B. Scramjet inlet control by off-body energy addition: A virtual cowl, AIAA Journal, 42(11): 374
4 H.Yan, D. Gaitonde. Numerical Study on Effect of a Thermal Bump in Supersonic Flow Control.AIAA.39th Plasmadynamic and Lasers Conference, 2008.Seattle USA, AIAA: 1-3
5 Nicholas J. Bisek, Iain D. Boyd. Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles. Journal of Spacecraft and Rockets. 2009, 46(3): 568-568
6 H. Yan, D. Gaitonde, J.S. Shang. Supersonic Flow Control by Pulsed Thermal Bump. 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008. AIAA, 2008: 1-15
7 K.Kontis. Flow Control effectiveness of jets, strakes, and flares at hypersonic speeds. J. of Aerospace Engineering. 222(Special Issue Paper): 585-588
8 Resler RL, Sears WR. The prospects for magneto-aerodynamics. J Aero Sci.. 1958, 25(4):235–45, 258
9 E.M. Braun, F.K.Lu, D.R.Wilson. Experimental research in aerodynamic control with electric and electromagnetic fields. Progress in Aerospace Sciences 2009, 45: 30-49
10 A.L. Kuranov and E.G. Sheikin, Magnetohydrodynamic Control on Hypersonic Aircraft under "AJAX" concept. J Space Rockets. 2003, 40(2):174-182
11 1E.G.Sheikin, A.L.Kuranov. MHD Control in Hypersonic Aircraft. 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reno USA, 2005. AIAA, 2005:1-3
12 A. Kuranov, A.Korabelnikov. Hypersonic technologies of atmospheric Cruise flight Under AJAX concept. 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Dayton, Ohio, USA, 2008.AIAA, 2008:1-5
13 Patrick RM. Magneto-hydrodynamics of compressible fluids. PhD dissertation, Cornell University, Ithaca, NY. 1956: 198
14 Simmons GA, Nelson GL. Overview of the NASA MARIAH project and summary of technical results. AIAA Albuquerque, NM. 1998. 1998-2752: 5-6
15 G. Candler and J. Perkins, Effect of Vibration Nonequilibrium on Axisymmetric Hypersonic Nozzle Design. 29th Aerospace Science Meeting,1991: 1-5
16 Joseph C. Yen, William R. Martindale, An Inviscid Supersonic Nozzle Design Approach to Perfect Flow Uniformity for Wind Tunnel Applications, 26th AIAA Applied Aerodynamics Conference, 2008: 1-3
17 C. Hirchen, P. Gruhn, A. Gülhan, Influence of Heat Capacity Ratio on the Interaction between the External Flow and Nozzle flow of a scramjet, 14th AIAA/AHI Space Planes and Hypersonic System and Technologies Conference, 2006. AIAA, 2006:1-2
18 Palm P, Meyer R, Ploenjes E, Bezant A, Adamovich IV, Rich JW, et al. MHD effect on a supersonic weakly ionized flow. AIAA Maui, HI; May 2002. AIAA, 2002-2246: 3-10
19 Macheret SO, Shneider MN, Miles RB. Modeling of plasma generation in repetitive ultra-short DC, microwave, and laser pulses. Anaheim, CA, USA, 2001. AIAA,2001-2940:5
20吕浩宇,李椿萱,董海涛.三维超声速磁流体发生器的流动特性.中国科学.2009,39(3):435-445
21郭国才.MHD推进的可能性.船电技术, 1995, (02):32
22马丹.提高磁流体推进器电磁效率的一种方法.船电技术.2005, (02): 40
23田正雨,张康平,潘沙,李桦.磁流体动力学斜激波控制数值模拟分析.力学季刊.2008, (01):13
24郑小梅,徐大军,蔡国飙.MHD能量旁路超燃冲压发动机可行性分析.北京航空航天大学学报.2004, (3):12
25潘勇,王江峰,伍贻兆.非结构网格高超声速MHD流场逆风格式数值模拟.宇航学报,2008, 3(01):23
26鲍文,唐井峰,于达仁.MHD-Arc-Ramjet联合循环与AJAX间的性能比较.宇航学报, 2007,(01).
27钟梓鹏,王雨培,宋文艳,邓远灏.超燃冲压发动机尾喷管流场研究.弹箭与制导学报.2005, (SA):27
28 Macheret S.O., Shneider M. N. Miles RB 2001. Phys. Plasmas,2001 (8):1518
29李弘,苏铁,欧阳亮,王慧慧,白小燕,陈志鹏,刘万东.电子束产生大尺度等离子体过程的数值模拟研究.物理学.2006,55(7):7052-7055
30 Chen Li-Hong, Gu HongBin, Zhang Xin-Yu. Experimental study on scramjet with cavity/strut configuration. J. of Engineering Thermophysics. 2007, 28(4):717-719
31张志斌;胡良元;林彬.超燃冲压发动机热防护结构的理论计算.航天制造技术.2008,(4):48-50
32贺元元,乐嘉陵,倪鸿礼.吸气式高超声速机体/推进一体化飞行器数值和试验研究.实验流体力学.2007,21(2):30-33
33韩省思,刘亮,叶桃红,朱旻明,陈义良.三种湍流对Scramjet燃烧室冷态流场的数值模拟.中国科学技术大学学报.2009,39(3):321-324
34肖志祥,符松.用RANSPLES混合方法研究超声速底部流动.计算物理.2009,26(2):223-224
35柳朝晖,贺铸,李瑞霞,郑楚光.各向同性湍流中颗粒引起湍流变动的直接模拟.工程热物理学报.2006.27(1):224
36彭涛,钱若军.大涡模拟(LES)理论研究述评.第八届全国现代结构工程学术研讨会论文集,2008.工业建筑.2008:602-605
37周连第.用两方程模型计算回转体尾部和尾流湍流流动的流线迭代法.力学学报, 1982,(03):226-229
38史峰,徐忠.k-ε两方程模型的改进及其应用.空气动力学学报, 1991,(02):261-263
39王运良,徐忠,苗永淼.使用不同壁面函数对紊流流场计算结果的影响.流体机械, 1993,(12) :26-29
40刘宜,张佳卉.质量出口边界条件在流场模拟中的应用.通用机械, 2005,(06) :81
41 M. N. Shneider, S. O. Macheret, S. H. Zaidi, I. G. Girgis, R. B. Miles. Virtual Shapes in Supersonic Flow Control with Energy Addition. Journal of Propulsion and Power. 2008, 24(5): 900-916
42 VanWie, D. M.,“Scramjet Inlets,”Scramjet Propulsion, edited by E. T. Curran and S. N. B. Murthy, Vol. 189, Progress in Astronautics andAeronautics, AIAA, Reston, VA, 2000, Chap. 7, pp. 447–511.
43 Itikawa, Y., Ichimura, A., Onda, K., Sakimoto, K., Takayanagi, K., Hatano, Y., Hayashi, M., Nashimura, M., Tsurubuchi, S. Cross Sections for Collisions of Electrons and Photons with Oxygen Molecules. J. Phys. Chem. 1989, 18(1):23-42.
44 Itikawa, Y., Hayashi, M., Ichimura, A., Onda, K., Sakimoto, K., Takayanagi, K., Nakamura, M., Takayanagi, T. Cross Sections for Collisions of Electrons and Photons with Nitrogen Molecules. J. Phys. Chem.1986, 15(3): 985-1010
45 Macheret, S.O., Shneider, M.N., and Miles, R.B.Magnetohydrodynamic Control of Hypersonic Flowand Scramjet Inlets Using Electron Beam Ionization.AIAA Journal. 2002, 40,(1): 74-81.
46 Macheret, S.O., Shneider, M.N., Miles, R.B., and Lipinski, R.J. Electron Beam Generated Plasmas in Hypersonic Magnetohydrodynamic Channels. AIAA Journal, 2001, 39(6): 1127-1136
47 Blom, J. H., Hanson, R. K. Double-Discharge Arrangement for CW Electrical Excitation of Supersonic Flows. Applied Physics Letters. 1975, 26(4): 190.
48 M. N. Shneider, Sergey O. Macheret, and Richard B. Miles. Analysis of Magnetohydrodynamic Control of Scramjet Inlets. AIAA Journal. 2004,42(11):2303-2310
49陈兵,徐旭,蔡国飘.二维超燃冲压发动机尾喷管优化设计.推进技术.2002(5):433
50李建平,宋文艳,陈亮.超燃冲压发动机尾喷管性能研究.机械设计与制造, 2008, (02) : 95-97