气动热环境试验及测量技术研究进展
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摘要
地面风洞试验和飞行试验是研究高超声速飞行器气动加热的主要手段。针对临近空间复杂气动外形高超声速飞行器气动热环境研究的需要,分析探讨了国内气动热试验及测量技术的发展情况。分析了临近空间高超声速飞行器外形特征以及飞行剖面、边界层转捩和气动热环境特性等,进而分析了气动热环境风洞试验模拟理论,介绍了适用于气动热研究的风洞试验设备及其模拟能力,重点讨论了适用于不同类型风洞的热流测量技术发展近况、存在的问题和发展趋势;在以长时间、高热流、高壁温为主要特征的高超声速飞行试验中,无法应用风洞环境下的热流测量技术,因而介绍了目前飞行试验中采用的气动热测量技术,讨论了根据结构温度反辨识表面热流存在的问题,以及热流传感器表面的"冷点效应"、表面催化特性等因素对飞行试验气动热测量的影响,提出了后续工作中应重点研究和解决的临近空间飞行器气动热环境测量技术问题。
Ground wind tunnel tests and flight tests are the primary means of obtaining pneumatic heating data.In this paper,the development of the domestic hypersonic aerodynamic test and the heat flux measurement technology is analyzed and discussed.Firstly,the shape characteristics,the flight profile,the boundary layer transition and the aerodynamic thermal environment characteristics of the adjacent space hypersonic vehicles are analyzed.On this basis,the wind tunnel test simulation theory of the aerodynamic thermal environment is analyzed,and the domestic application for aerodynamic thermal measurement,wind tunnel test equipment and its simulation capability are introduced,focusing on the analysis of the development and trend of wind tunnel aerodynamic thermal environment measurement technology,including point measurement technology based on sensor measurement and non-contact measurement technology such as phosphorescence heat map technology and infrared heat map technology.Finally,the measurement principle and engineering application of the "built-in"and "embedded"measurement technologies are introduced for the flight test thermal environment measurement.The problems faced by the flight test aerodynamic thermal environment measurement are discussed.Both further research and present problems for thermal environment measurement technologies are proposed.
Ground wind tunnel tests and flight tests are the primary means of obtaining pneumatic heating data.In this paper,the development of the domestic hypersonic aerodynamic test and the heat flux measurement technology is analyzed and discussed.Firstly,the shape characteristics,the flight profile,the boundary layer transition and the aerodynamic thermal environment characteristics of the adjacent space hypersonic vehicles are analyzed.On this basis,the wind tunnel test simulation theory of the aerodynamic thermal environment is analyzed,and the domestic application for aerodynamic thermal measurement,wind tunnel test equipment and its simulation capability are introduced,focusing on the analysis of the development and trend of wind tunnel aerodynamic thermal environment measurement technology,including point measurement technology based on sensor measurement and non-contact measurement technology such as phosphorescence heat map technology and infrared heat map technology.Finally,the measurement principle and engineering application of the "built-in"and "embedded"measurement technologies are introduced for the flight test thermal environment measurement.The problems faced by the flight test aerodynamic thermal environment measurement are discussed.Both further research and present problems for thermal environment measurement technologies are proposed.
引文
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[21]张扣立,周嘉穗,孔荣宗,等.CARDC激波风洞TSP技术研究进展[J].空气动力学学报,2016,34(6):738-743.Zhang K L,Zhou J H,Kong R Z,et al.Development of TSPtechnique in shock tunnel of CARDC[J].Acta Aerodynamica Sinica,2016,34(6):738-743.
[22]张扣立,常雨,孔荣宗,等.温敏漆技术及其在边界层转捩测量中的应用[J].宇航学报,2013,34(6):860-865.Zhang K L,Chang Y,Kong R Z,et al.Temperature sensitive paint technique and its application in measurement of boundary layer transition[J].Journal of Astronautics,2013,34(6):860-865.
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[24]Stainback P C,Johnson C B,Boney L B,et al.Comparison of theoretical predictions and heat-transfer measurements for a flight experiment at Mach 20(reentry F)[R].NASA TM X-2560,1972.
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[26]刘初平.气动热与热防护试验热流测量[M].北京:国防工业出版社,2013.
[27]国义军,周宇,肖涵山,等.飞行试验热流辨识和边界层转捩滞后现象[J].航空学报,2017,38(10):121255.Guo Y J,Zhou Y,Xiao H S,et al.Delay phenomenon of boundary layer transition according to heating flux identified from flight test[J].Acta Aeronautica et Astronautica Sinica,2017,38(10):121255.
[28]钱炜祺,周宇,何开锋,等.考虑烧蚀情况下的表面热流辨识[J].空气动力学学报,2014,32(6):772-776.Qian W Q,Zhou Y,He K F,et al.Heat flux estimation for heat transfer problem with ablation[J].Acta Aerodynamica Sinica,2014,32(6):772-776.
[29]钱炜祺,周宇,何开锋,等.表面热流辨识技术在边界层转捩位置测量中的应用初步研究[J].实验流体力学,2012,26(1):74-78.Qian W Q,Zhou Y,He K F,et al.A preliminary study for application of surface heat flux estimation technology in transition measurement[J].Journal of Experiments in Fluid Mechanics,2012,26(1):74-78.
[30]何开锋,汪清,钱炜祺,等.高超声速飞行器气动力/热参数辨识研究综述[J].实验流体力学,2011,25(5):99-104.He K F,Wang Q,Qian W Q,et al.Review of aerodynamic and aero-thermodynamic parameter estimation research for hypersonic aircraft[J].Journal of Experiments in Fluid Mechanics,2011,25(5):99-104.
[31]Kandula M,Reinarts T.Corrections for convective heat flux gauges subjected to a surface temperature discontinuity[R].AIAA-2002-3087,2002.
[32]孟松鹤,丁小恒,易法军,等.高超声速飞行器表面测热技术综述[J].航空学报,2014,35(7):1759-1775.Meng S H,Ding X H,Yi F J,et al.Overview of heat measurement technology for hypersonic vehicle surfaces[J].Acta Aeronautica et Astronautica Sinica,2014,35(7):1759-1775.
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[34]孟松鹤,金华,王国林,等.热防护材料表面催化特性研究进展[J].航空学报,2014,35(2):287-302.Meng S H,Jin H,Wang G L,et al.Research advances on surface catalytic properties of thermal protection materials[J].Acta Aeronautica et Astronautica Sinica,2014,35(2):287-302.
[35]丁明松,董维中,高铁锁,等.传感器催化特性差异对气动热影响的计算分析[J].宇航学报,2017,38(12):1361-1371.Ding M S,Dong W Z,Gao T S,et al.Computational analysis of influence on aero thermal environments caused by catalytic property distinction of heat flux sensor[J].Journal of Astronautics,2017,38(12):1361-1371.
[2]Johnson C B;Kaufman L GⅢ.High speed interference heating loads and pressure distributions resulting from elevon deflections(shock wave interaction effects on hypersonic aircraft surfaces)[C]//Proc of the 17th Aerospace Sciences Meeting.1979.
[3]Schuricht P H.Roberts G T.Hypersonic interference heating induced by a blunt fin[C]//Proc of the 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.1998.
[4]潘宏禄,李俊红,张学军.突起物及其干扰区热环境影响范围分析[J].计算物理,2013,30(6):825-832.Pan H L,Li J H,Zhang X J.Analysis on thermal environment of interaction region around protuberance in high speed flows[J].Chinese Journal of Computational Physics,2013,30(6):825-832.
[5]周佳.高超声速飞行器钝舵缝隙气动热环境研究[D].绵阳:西南科技大学,2017.Zhou J.Study of aerodynamic heating environment on blunt-fin gap of hypersonic vehicle[D].Mianyang:Southwest University of Science and Technology,2017.
[6]董维中,高铁锁,丁明松,等.高超声速飞行器表面温度分布与气动热耦合数值研究[J].航空学报,2015,36(1):311-324.Dong W Z,Gao T S,Ding M S,et al.Numerical study of coupled surface temperature distribution and aerodynamic heat for hypersonic vehicles[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):311-324.
[7]董维中,丁明松,高铁锁,等.热化学非平衡模型和表面温度对气动热计算影响分析[J].空气动力学学报,2013,31(6):692-698.Dong W Z,Ding M S,Gao T S,et al.The influence of thermochemical non-equilibrium model and surface temperature on heat transfer rate[J].Acta Aerodynamica Sinica,2013,31(6):692-698.
[8]丁明松,董维中,高铁锁,等.局部催化特性差异对气动热环境影响的计算分析[J].航空学报,2018,39(3):44-54.Ding M S,Dong W Z,Gao T S,et al.Computational analysis of influence of differences in local catalytic properties on aerothermal environment[J].Acta Aeronautica et Astronautica Sinica,2018,39(3):44-54.
[9]王庆洋,丛堃林,刘丽丽,等.临近空间高超声速飞行器气动力及气动热研究现状[J].气体物理,2017,2(4):46-55.Wang Q Y,Cong K L,Liu L L,et al.Research status on aerodynamic force and heat of near space hypersonic flight vehicle[J].Physics of Gases,2017,2(4):46-55.
[10]王智慧,鲍麟,童秉纲.尖化前缘的稀薄气体化学非平衡流动和气动加热相似律研究[J].气体物理,2016,1(1):5-12.Wang Z H,Bao L,Tong B G.Similarity law of aero-heating to sharpened noses in rarefiedchemical nonequilibrium flows[J].Physics of Gases,2016,1(1):5-12.
[11]余平,段毅,尘军.高超声速飞行的若干气动问题[J].航空学报,2015,36(1):7-23.Yu P,Duan Y,Chen J,Some aerodynamic issues in hypersonic flight[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):7-23.
[12]国义军,曾磊,张昊元,等.HTV2第二次飞行试验气动热环境及失效模式分析[J].空气动力学学报,2017,35(4):496-503.Guo Y J,Zeng L,Zhang H Y,et al.Investigation on aerothermodynamic environment and ablation which lead to HTV-2second fight test failing[J].Acta Aerodynamica Sinica,2017,35(4):496-503.
[13]任思根.实验空气动力学[M].北京:宇航出版社,1996.
[14]彭治雨,石义雷,龚红明,等.高超声速气动热预测技术及发展趋势[J].航空学报,2015,36(1):325-345.Peng Z Y,Shi Y L,Gong H M,et al.Hypersonic aeroheating prediction technique and its trend of development[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):325-345.
[15]涂建强,刘德英,陈海群.长时间隔热材料环境的稳态热流测量方法[J].宇航材料工艺,2008,38(2):76-80.Tu J Q,Liu D Y,Chen H Q.Steady-state heat-flux measurement method for environment of long-time insulation materials[J].Aerospace materials&technology,2008,38(2):76-80.
[16]李强,刘济春,孔荣宗.耐冲刷薄膜铂电阻热流传感器研制[J].电子测量与仪器学报,2017,31(4):623-629.Li Q,Liu J C,Kong R Z.Development of anti-erosion platinum thin film resistance thermal sensor[J].Journal of Electronic Measurement and Instrumentation,2017,31(4):623-629.
[17]秦峰,何川,曾磊,等.驻点热流测量试验技术研究[J].西南交通大学学报,2013,48(6):1072-1077.Qin F,He C,Zeng L,et al.Experimental research of heattransfer measurements on stagnation points[J].Journal of Southwest Jiaotong University,2013,48(6):1072-1077.
[18]陈星.尖化前缘热环境实验技术研究[D].长沙:国防科技大学,2011.Chen X.Experimental technique study of heat transfer measurement on sharp leading edges[D].Changsha:National University of Defense Technology,2011.
[19]王兴虎.同轴热电偶的响应特性分析与实验研究[D].北京:中国科学院大学,2018.Wang X H.Analysis of response characteristics and experimental research of coaxial thermocouple[D].Beijing:University of Chinese Academy of Sciences,2018.
[20]毕志献,韩曙光,伍超华,等.磷光热图测热技术研究[J].实验流体力学,2013,27(3):87-92.Bi Z X,Han S G,Wu C H,et al.Phosphor thermography study in gun tunnel[J].Journal of Experiments in Fluid Mechanics,2013,27(3):87-92.
[21]张扣立,周嘉穗,孔荣宗,等.CARDC激波风洞TSP技术研究进展[J].空气动力学学报,2016,34(6):738-743.Zhang K L,Zhou J H,Kong R Z,et al.Development of TSPtechnique in shock tunnel of CARDC[J].Acta Aerodynamica Sinica,2016,34(6):738-743.
[22]张扣立,常雨,孔荣宗,等.温敏漆技术及其在边界层转捩测量中的应用[J].宇航学报,2013,34(6):860-865.Zhang K L,Chang Y,Kong R Z,et al.Temperature sensitive paint technique and its application in measurement of boundary layer transition[J].Journal of Astronautics,2013,34(6):860-865.
[23]李明,祝智伟,李志辉.红外热图在高超声速低密度风洞测热试验中的应用概述[J].实验流体力学,2013,27(3):108-112.Li M,Zhu Z W,Li Z H.The summarization of infrared thermography on aerodynamic heating measurement in hypersonic low density wind tunnel[J].Journal of Experiments in Fluid Mechanics,2013,27(3):108-112.
[24]Stainback P C,Johnson C B,Boney L B,et al.Comparison of theoretical predictions and heat-transfer measurements for a flight experiment at Mach 20(reentry F)[R].NASA TM X-2560,1972.
[25]Kimmel R L,Adamczak D,Borg M P,et al.HIFiRE-1and HIFiRE-5test results[R].DTIC ADA605731,2014.
[26]刘初平.气动热与热防护试验热流测量[M].北京:国防工业出版社,2013.
[27]国义军,周宇,肖涵山,等.飞行试验热流辨识和边界层转捩滞后现象[J].航空学报,2017,38(10):121255.Guo Y J,Zhou Y,Xiao H S,et al.Delay phenomenon of boundary layer transition according to heating flux identified from flight test[J].Acta Aeronautica et Astronautica Sinica,2017,38(10):121255.
[28]钱炜祺,周宇,何开锋,等.考虑烧蚀情况下的表面热流辨识[J].空气动力学学报,2014,32(6):772-776.Qian W Q,Zhou Y,He K F,et al.Heat flux estimation for heat transfer problem with ablation[J].Acta Aerodynamica Sinica,2014,32(6):772-776.
[29]钱炜祺,周宇,何开锋,等.表面热流辨识技术在边界层转捩位置测量中的应用初步研究[J].实验流体力学,2012,26(1):74-78.Qian W Q,Zhou Y,He K F,et al.A preliminary study for application of surface heat flux estimation technology in transition measurement[J].Journal of Experiments in Fluid Mechanics,2012,26(1):74-78.
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