高超声速飞行器脆性透波材料大热流冲击下断裂性能试验
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摘要
高超声速飞行器在俯冲段、高机动变轨或瞬间外露定位探测设备时,快速变化的高热流密度气动热会对天线窗、天线罩等部件产生强烈的热冲击。判断脆性材料透波部件在大热流密度冲击下是否出现断裂破坏及确定断裂时间点,对于高超声速飞行器能否最终锁定并击中目标具有极为重要的意义。本文建立石英灯红外辐射式大热流冲击试验系统,最大冲击热流密度可达1.5MW/m~2,并对SiO_2和Al_2O_32种脆性材料进行了高速热冲击试验。热流冲击模拟准确,控制结果与预设热流的相对误差小于1.0%。同时,采用数字图像相关方法实时采集热冲击过程中脆性材料表面散斑图像的动态变化,成功捕捉并获得了断裂时间点这一重要关键参数。通过对散斑图像的分析计算,得到了脆性试验件断裂前的表面应变的变化。试验结果为高超声速飞行器透波天线窗等信号探测定位部件在高速大热流热冲击下的安全可靠性设计提供了重要依据。
When the hypersonic vehicle is in the stage of subduction,high maneuver orbital changing or instantaneous revealing of the location detection equipment,the fast variation of high-heat-flow aerodynamic heating will produce severe thermal shock to the components,such as antenna windows and radome.It is very important for the hypersonic vehicle to determine whether the breakage occurs under the shock of the large heat flux and obtain its fracture time,because the results have great significance to hypersonic vehicle to finally lock up and hit the target.In this paper,aquartz lamp infrared radiation high-heat-flow thermal shock test system was established,and the maximum heat flux of the test system is up to 1.5 MW/m~2.High speed thermal shock experiments of brittle materials(SiO_2 and Al_2 O_3)were performed.The thermal shock simulation is accurate,and the relative error between the controlled result and the pre-set heat flow is less than 1.0%.In addition,using the digital image correlation method,the dynamic changes of speckle image on brittle material surface were recorded in real time during the thermal shock process,and the important data of fracture time were successfully captured.Through analyzing and calculating speckle images,the changes of strain on the surface were obtained before the fracture of the specimen.The experimental results provide an important basis for the safety and reliability design of the signal detection and locking device for hypersonic vehicle,such as permeable antenna window,under high speed and high-heat-flow thermal shocks.
When the hypersonic vehicle is in the stage of subduction,high maneuver orbital changing or instantaneous revealing of the location detection equipment,the fast variation of high-heat-flow aerodynamic heating will produce severe thermal shock to the components,such as antenna windows and radome.It is very important for the hypersonic vehicle to determine whether the breakage occurs under the shock of the large heat flux and obtain its fracture time,because the results have great significance to hypersonic vehicle to finally lock up and hit the target.In this paper,aquartz lamp infrared radiation high-heat-flow thermal shock test system was established,and the maximum heat flux of the test system is up to 1.5 MW/m~2.High speed thermal shock experiments of brittle materials(SiO_2 and Al_2 O_3)were performed.The thermal shock simulation is accurate,and the relative error between the controlled result and the pre-set heat flow is less than 1.0%.In addition,using the digital image correlation method,the dynamic changes of speckle image on brittle material surface were recorded in real time during the thermal shock process,and the important data of fracture time were successfully captured.Through analyzing and calculating speckle images,the changes of strain on the surface were obtained before the fracture of the specimen.The experimental results provide an important basis for the safety and reliability design of the signal detection and locking device for hypersonic vehicle,such as permeable antenna window,under high speed and high-heat-flow thermal shocks.
引文
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[2]MENG S H,YANG Q,XIE W H,et al.Structure redesign of the integrated thermal protection system and fuzzy performance evaluation[J].AIAA Journal,2016,54(11):3598-3607.
[3]梁强,许泉,阳华.红外头罩电弧风洞试验状态的量化新判据[J].上海航天,2013,30(3):11-15.LIANG Q,XU Q,YANG H.A new quantified criterion to arc heated wind tunnel test of infrared dome[J].Aerospace Shanghai,2013,30(3):11-15(in Chinese).
[4]王保林,韩杰才,杜善义.热冲击作用下基底/涂层结构的应力分析及结构优化[J].复合材料学报,1999,16(1):125-130.WANG B L,HAN J C,DU S Y.Thermal stress analysis and optimization of substrate/coating structure under thermal shock[J].Acta Materiae Compositae Sinica,1999,16(1):125-130(in Chinese).
[5]QU Z,CHENG X,HE R,et al.Rapid heating thermal shock behavior study of CVD ZnS infrared window material:Numerical and experimental study[J].Journal of Alloys&Compounds,2016,682:565-570.
[6]PETTERSSON P,JOHNSSON M,SHEN Z.Parameters for measuring the thermal shock of ceramic materials with an indentation-quench method[J].Journal of the European Ceramic Society,2002,22(11):1883-1889.
[7]CHEN L,WANG A,SUO X,et al.Effect of surface heat transfer coefficient gradient on thermal shock failure of ceramic materials under rapid cooling condition[J].Ceramics International,2018,44(8):8992-8999.
[8]HE R,QU Z,LIANG D.Rapid heating thermal shock study of ultra high temperature ceramics using an in situ,testing method[J].Journal of Advanced Ceramics,2017,6(4):279-287.
[9]PANDA P K,KANNAN T S,DUBOIS J,et al.Thermal shock and thermal fatigue study of alumina[J].Journal of the European Ceramic Society,2002,22(13):2187-2196.
[10]CHU P,MARKSBERRY C,SAARI D.High temperature storage heater technology for hypersonic wind tunnels and propulsion test facilities[C]∥13th AIAA/CIRA International Space Planes and Hypersonics Systems and Technologies Conference.Reston,VA:AIAA,2005:1-15.
[11]BOUSLOG S,MOORE B,LAWSON I,et al.X-33metallic TPS tests in NASA-LARC high temperature tunnel:AIAA-99-1045[R].Reston,VA:AIAA,1999.
[12]ZIEMKE R A.Infrared heater used in qualification testing of international space station radiators:NASA/TM 2004-212332[R].Washington,D.C.:NASA,2004.
[13]BAI D,FAN X J.Transient coupled heat transfer in multilayer non-gray semitransparent media with reflective foils[J].International Journal of Thermophysics,2006,27(2):647-664.
[14]DARYABEIGI K.Thermal analysis and design of multilayer insulation for re-entry aerodynamic heating[J].Journal of Spacecraft&Rockets,2001,39(4):509-514.
[15]NASA Flight Loads Lab.Thermal and Cryogenic Systems.(2017-08-04)[2018-07-30].https:∥www.nasa.gov/centers/armstrong/research/Facilities/FLL/therm.html
[16]任青梅.热/结构试验技术研究进展[J].飞航导弹,2012,2:91-96.REN Q M.Overview of thermal/structural test technology[J].Winged Missiles Journal,2012,2:91-96(in Chinese).
[17]吴大方,王怀涛,朱芳卉.1 200℃高温环境下部件受热前表面应变的光学测量[J].应用数学和力学,2018,39(6):631-644.WU D F,WANG H T,ZHU F H.Optical measurement of heated-front-surface strains for components in high temperature environments up to 1 200℃[J].Applied Mathematics and Mechanics,2018,39(6):631-644(in Chinese).
[18]吴大方,潘兵,高镇同,等.超高温、大热流、非线性气动热环境试验模拟及测试技术研究[J].实验力学,2012,27(3):255-271.WU D F,PAN B,GAO Z T,et al.On the experimental simulation of ultra-high temperature,high heat flux and nonlinear aerodynamic heating environment and thermomechanical testing technique[J].Journal of Experimental Mechanics,2012,27(3):255-271(in Chinese).
[19]WU D F,WANG Y W,SHANG L,et al.Experimental and computational investigations of thermal modal parameters for a plate-structure under 1 200℃high temperature environment[J].Measurement,2016,94:80-91.
[20]WU D F,WANG Y W,SHANG L,et al.Thermo-mechanical properties of C/SiC composite structure under extremely high temperature environment up to 1 500℃[J].Composite Part B:Engineering,2016,90:424-431.
[21]PETERS W H,RANSON W F.Digital imaging techniques in experimental stress analysis[J].Optical Engineering,1982,21(3):427-431.
[22]BRUCK H A,MCNEILL S R,SUTTON M A,et al.Digital image correlation using Newton-Raphson method of partial differential correction[J].Experimental Mechanics,1989,29(3):261-267.
[23]TONG W.An evaluation of digital image correlation criteria for strain mapping applications[J].Strain,2005,41(4):167-175.