高超声速弹箭头部气动热数值计算
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摘要
本文对稠密大气层中飞行的高超声速弹箭(马赫数Ma=5～8),采用工程近似计算和数值模拟相结合的方法,计算分析弹箭头部气动加热及内部温度场分布。
对于钝头旋成体层流边界层的加热问题,首先采用费-里德尔(Fay-Riddle)平衡边界层驻点热流密度公式计算头部驻点热流密度,然后采用Lees方法将弹箭头部热流密度用驻点热流密度归一化表示。在数值离散时,将热流公式线性化成壁面温度的函数关系式,并作为弹箭头部温度场数值模拟的边界条件。
在弹体内部,采用有限体积方法,二阶精度,全隐格式,在非结构化网格上离散三维非稳态导热方程。由于网格的非正交性和高精度要求,同时交替计算一次扩散项(法向分量)和二次扩散项(切向分量)。程序编写采用Fortran95语言,模块化完成二维和三维程序的编制;并且实现了网格前处理的多功能化,可以与通用商用软件Tecplot和Gambit进行直接对接。
最后,在充分验证程序的正确性后,将热环境的工程算法和温度场数值模拟相耦合,对两种不同的弹头模型进行弹箭头部温度场的数值模拟,得到最高温度分布区间和动态温度场变化规律。计算结果表明:来流马赫数、头部球头的直径等是影响气动热的重要因素。本文结果正确可信并具有一定的实用价值,可供工程设计人员参考。
The aerodynamic heating and temperature fields of hypersonic projectile's head (Ma=5 ~ 8) in denseness aerosphere were calculated by using the engineering and numerical simulation methods.
At the firstly, the Fay-Riddle balance boundary layer stagnation point heat flux formula is applied in computation the stagnation point heat flux of blunt head. Secondly, the heat flux of projectile's head has been unitary expressed by Lees' method. The heat flux formulas have been linearized and expressed as the function of the temperature of projectile's wall in numerical discretization process, and be treated as the boundary conditions of temperature field's numerical simulation.
By using the finite volume method (FVM), second-order accuracy, full implicitly format discretizing the three dimensions unsteady state heat conduction equations in unstructured grid. For meeting the grid orthogonality and high precision, calculating the first diffusion (the normal direction) and second diffusion (the tangent direction ) alternately at the same time. The program has been compiled by Fortran95, and realized multifunction of the grid pre-treatment through connected with the commercial software such as Tecplot and Gambit.
The engineering method of heat environment and numerical simulation of temperature field are coupling at full validating program's correctness. For simulating the temperature field of two different geometries projectile's head, the tiptop temperature distribution and change rule of dynamic temperature field have been gained.
The results indicate that the inlet Mach number and the diameter of projectile's ball head are important factors of aerodynamic heating. The results are rewarding engineer to reference.
对于钝头旋成体层流边界层的加热问题,首先采用费-里德尔(Fay-Riddle)平衡边界层驻点热流密度公式计算头部驻点热流密度,然后采用Lees方法将弹箭头部热流密度用驻点热流密度归一化表示。在数值离散时,将热流公式线性化成壁面温度的函数关系式,并作为弹箭头部温度场数值模拟的边界条件。
在弹体内部,采用有限体积方法,二阶精度,全隐格式,在非结构化网格上离散三维非稳态导热方程。由于网格的非正交性和高精度要求,同时交替计算一次扩散项(法向分量)和二次扩散项(切向分量)。程序编写采用Fortran95语言,模块化完成二维和三维程序的编制;并且实现了网格前处理的多功能化,可以与通用商用软件Tecplot和Gambit进行直接对接。
最后,在充分验证程序的正确性后,将热环境的工程算法和温度场数值模拟相耦合,对两种不同的弹头模型进行弹箭头部温度场的数值模拟,得到最高温度分布区间和动态温度场变化规律。计算结果表明:来流马赫数、头部球头的直径等是影响气动热的重要因素。本文结果正确可信并具有一定的实用价值,可供工程设计人员参考。
The aerodynamic heating and temperature fields of hypersonic projectile's head (Ma=5 ~ 8) in denseness aerosphere were calculated by using the engineering and numerical simulation methods.
At the firstly, the Fay-Riddle balance boundary layer stagnation point heat flux formula is applied in computation the stagnation point heat flux of blunt head. Secondly, the heat flux of projectile's head has been unitary expressed by Lees' method. The heat flux formulas have been linearized and expressed as the function of the temperature of projectile's wall in numerical discretization process, and be treated as the boundary conditions of temperature field's numerical simulation.
By using the finite volume method (FVM), second-order accuracy, full implicitly format discretizing the three dimensions unsteady state heat conduction equations in unstructured grid. For meeting the grid orthogonality and high precision, calculating the first diffusion (the normal direction) and second diffusion (the tangent direction ) alternately at the same time. The program has been compiled by Fortran95, and realized multifunction of the grid pre-treatment through connected with the commercial software such as Tecplot and Gambit.
The engineering method of heat environment and numerical simulation of temperature field are coupling at full validating program's correctness. For simulating the temperature field of two different geometries projectile's head, the tiptop temperature distribution and change rule of dynamic temperature field have been gained.
The results indicate that the inlet Mach number and the diameter of projectile's ball head are important factors of aerodynamic heating. The results are rewarding engineer to reference.
引文
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[34]王福军.计算流体动力学分析.北京:清华大学出版社,2004
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[46]商立英.非结构化网格上非稳态问题的求解与应用.南京理工大学硕士学位论文,2006
[47]武淑萍,张敏,商立英.结构化与非结构化网格中的导热计算.南京工程学院学报(自然科学版),第3卷第2期,2005.3(2):11-16
[48]王昌凌,王弘.导热三维温度场的科学计算可视化研究.华中理工大学学报,1997,25(6):63-66
[49]杨永健,张来平,高树椿,张涵信.非结构网格、混合网格下计算方法研究.空气动力学学报,2003,21(2):144-150
[50]刘晓燕,吴国忠,庞丽萍,高德生.网格划分对传热模拟计算的影响.大庆石油学院学报,1999,23(4)
[51]宇波,林明杰,王秋旺,陶文铨.一种非结构化同位网格算法.工程热物理学报,1998,19(4):475-479
[52]张洪济.热传导.高等教育出版社,1990
[53]M.N.奥齐西克 著,俞吕铭 译.热传导.高等教育出版社,1984
[54]黄志澄.空天飞机气动热的工程预测方法.气动实验与测量,1992,6(1):1-8
[55]沈遐龄.航天飞机气动加热计算.北京航空航天大学学报,1998,24(2):189-192
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[2]Heins A E,Estes T J.Effect of Angle Attack on Laminar Convective Heating Transfer on Sharp and Blunt Cones.AD-600628
[3]MarvinJ G.Turbulence Modeling for Computational Aerodynamics.AIAA Journal,1983,21(7).941-955
[4]Alireza,Najafiyazdi.An Engineering Inviscid-Reacting Boundary Layer Method for Calculation of Hypersonic Aerodynamic Heating.43rd AIAA Aerospace Sciences Meeting and Exhibit
[5]夏丰领,陈国光.高速火箭弹的气动加热计算.华北工学院学报,2003,24(6)
[6]赵梦熊.载人飞船返回舱的气动热流分布.气动实验与测量,1996,10(1):1-8
[7]雷延花.高超声速飞行器气动特性计算方法研究.西安:西北工业大学硕士论文,2000
[8]刘仙名.空空导弹气动加热理论及其应用.航空兵器,1997(2):22-25
[9]陈志敏,雷延花.天地往返运输器气动力和气动热工程计算方法研究.西北工业大学学报,2001,19(2):205-208
[10]史金光,王中原.弹翼表面气动加热和烧蚀现象的研究.弹道学报,2001,13(2),41-44
[11]范晓樯,李桦等.钝头双锥体有攻角表面热流计算密度.兵工学报,2002,23(1):142-144
[12]尹莲花,刘莉,张帅.近程高速弹头的温度场与热应力数值仿真研究.系统仿真学报,2008.20(5)
[13]Patankar,S V.Numerical Heat Transfer and Fluid Flow,Hemisphere Publishing,1981
[14]B.F.Blackwell,R.E.Hogan.Numerical Solution of 2-D Axisymmetric Heat Conduction Problems Using a Finite Volume Technique.AIAA 26th Thermophsics conference
[15]B.T.F.Chung and T.Y.Chang.Heat Transfer in Solids with Variable Thermal Properties and Orthotropic Conductivity.AIAA 16th Thermophysics Conference
[16]Dechaumphai P,Thornton E A,Wieting A.R..Flow-thermal-structural study of aerodynamically heated leading edges.AIAA 88-2245
[17]陈兰,胡汉东.数值求解瞬态温度场的有限体积法.工程热物理学报,2001,22
[18]成楚之.国内外导弹热结构分析研究综述.现代防御技术,1998,26(6)
[19]罗志伟,孟范源,郑钢铁.一种导弹隔热层内传热计算的近似方法.战术导弹技术,2004(1):24-29
[20]王宝国,刘淑艳,黄伟光.气体动力学.北京理工大学出版社,2004
[21]钱翼稷.空气动力学.北京航空航天大学出版社,2005
[22]黄志澄.高超声速飞行器空气动力学.北京:国防工业出版社,1995
[23]姜贵庆.刘连元.高速气流传热与烧蚀热防护.北京,国防工业出版社,2003
[24]张志成.高超声速气动热和热防护.北京,国防工业出版社,2003
[25]赵梦熊.载人飞船空气动力学.北京,国防工业出版社,2000
[26]李凰立.再入弹头的气动加热及热响应分析.西安:西北工业大学硕士论文,2001
[27]瞿章华,曾明.高超声速空气动力学.长沙,国防科技大学出版社,1999
[28]卞荫贵,徐立功.气动热力学.第1版.北京:中国科技大学出版社,1997
[29]张鲁民.载人飞船返回舱空气动力学.北京:国防工业出版社,2002
[30]王瑞金,张凯,王刚.Fluent技术基础与应用实例.北京:清华大学出版社,2007
[31]韩古忠,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
[32]刘晶.结构与非结构化网格的生成、转换及应用.南京:南京理工大学硕士论文,2006
[33]李人宪.有限体积法基础.北京:国防工业出版社,2005
[34]王福军.计算流体动力学分析.北京:清华大学出版社,2004
[35]Zhang,M.Modeling of Radiative Heat Transfer and Diffusion Processes Using Unstructured Grid.Ph.D.Tennessee Technological University,USA.2000.
[36]黄庆宏,张敏,刘晶.非结构化网格特定条件下热传导的数值计算.南京师范大学学报(工程技术版),2006,6(3):26-30
[37]张敏,戴春林,范悦宏.圆环域中结构与非结构网格的热传导数值计算.东北电力学院学报(自然科学版),2004,24(6):15-19
[38]Chai,J.C.,Zhang,M.Moder,J.P.,and Patankar,S.V.Conduction Heat Transfer Calculations Using Structured and Unstructured Grids.ICHMT Symposium CHT'01 - Advances in Numerical Heat Transfer.2001(1):519-526
[39]陶文铨.数值传热学.西安:西安交通大学出版社,2001.
[40]陶文铨.计算传热学的近代进展.北京:科学出版社,2001
[41]Suhas V.Patankar.Computation of Conduction and Duct Flow Heat Transfer.Innovative Research,Inc.7846 Ithaca Lane North Maple Grove,MN55369-8549,USA
[42]王希季.航天器进入与返回技术.北京:中国宇航出版社,2007
[43]杨世铭,陶文铨.传热学.北京:高等教育出版社,1998
[44]张家荣,赵廷元.工程常用物质的热物理性质手册.北京:新时代出版社,1987
[45]Patankar,S.V.Numerical Heat Transfer and Fluid Flow,Hemisphere Publishing,1981
[46]商立英.非结构化网格上非稳态问题的求解与应用.南京理工大学硕士学位论文,2006
[47]武淑萍,张敏,商立英.结构化与非结构化网格中的导热计算.南京工程学院学报(自然科学版),第3卷第2期,2005.3(2):11-16
[48]王昌凌,王弘.导热三维温度场的科学计算可视化研究.华中理工大学学报,1997,25(6):63-66
[49]杨永健,张来平,高树椿,张涵信.非结构网格、混合网格下计算方法研究.空气动力学学报,2003,21(2):144-150
[50]刘晓燕,吴国忠,庞丽萍,高德生.网格划分对传热模拟计算的影响.大庆石油学院学报,1999,23(4)
[51]宇波,林明杰,王秋旺,陶文铨.一种非结构化同位网格算法.工程热物理学报,1998,19(4):475-479
[52]张洪济.热传导.高等教育出版社,1990
[53]M.N.奥齐西克 著,俞吕铭 译.热传导.高等教育出版社,1984
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