高超声速非平衡气动加热试验及数值分析研究
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摘要
高超声速非平衡流动气动加热的精确预测是当前高超声速飞行器热防护设计面临的难点和热点问题.设计了外形简单的球柱测热模型,采用表面溅射金Au和二氧化硅SiO_2的方法改变了模型和塞式量热计表面的催化特性,并在电弧风洞中开展了高超声速非平衡流动气动加热试验,获得了近完全催化壁及近非催化壁两种条件下模型表面的气动加热数据.通过和数值模拟结果对比分析,对高温化学非平衡气动加热的数值预测方法进行了验证,结果表明:表面材料的催化特性对非平衡气动加热有显著影响,测热模型的球面上催化效应影响明显,完全催化热流要高于非催化热流,而柱面上催化效应较弱;数值模拟得到的不同壁面催化条件之间热流差异大于地面试验结果;计算结果与试验结果相比,完全催化壁热流相差在5%以内,完全非催化壁热流相差超过10%.
In the design of hypersonic vehicle thermal protection, precise prediction on the non-equilibrium aerodynamic heating in condition of hypersonic flow has been recognized as the difficult and hot topic in the current academic and engineering field. In this paper, a simple spherical column thermal model was designed. The surface catalytic properties of the model and plug-type calorimeter were changed by sputtering Au and Si O2 on the surface. In the arc tunnel, a hypersonic non-equilibrium flow aerodynamic heating test was carried out to obtain the aerodynamic heating data of the model surface under both near complete catalysis and near non-catalysis.Based on the comparative analysis of test results and numerical calculation results, the numerical prediction method of high temperature chemical non-equilibrium aerodynamic heating is validated. The results show that the catalytic properties of the surface material have a significant effect on the non-equilibrium aerodynamic heating; the catalytic effect on the spherical surface is obvious,the complete catalytic heating is higher than the non-catalytic heating, but the catalytic effect on the cylinder surface is weaker. The numerical simulation results show that the difference of the heat flux between the different wall catalytic conditions is greater than that of the ground test results; completely catalytic wall heat flux within 5% of the difference, completely non-catalytic wall heat flux difference of more than 10%.
In the design of hypersonic vehicle thermal protection, precise prediction on the non-equilibrium aerodynamic heating in condition of hypersonic flow has been recognized as the difficult and hot topic in the current academic and engineering field. In this paper, a simple spherical column thermal model was designed. The surface catalytic properties of the model and plug-type calorimeter were changed by sputtering Au and Si O2 on the surface. In the arc tunnel, a hypersonic non-equilibrium flow aerodynamic heating test was carried out to obtain the aerodynamic heating data of the model surface under both near complete catalysis and near non-catalysis.Based on the comparative analysis of test results and numerical calculation results, the numerical prediction method of high temperature chemical non-equilibrium aerodynamic heating is validated. The results show that the catalytic properties of the surface material have a significant effect on the non-equilibrium aerodynamic heating; the catalytic effect on the spherical surface is obvious,the complete catalytic heating is higher than the non-catalytic heating, but the catalytic effect on the cylinder surface is weaker. The numerical simulation results show that the difference of the heat flux between the different wall catalytic conditions is greater than that of the ground test results; completely catalytic wall heat flux within 5% of the difference, completely non-catalytic wall heat flux difference of more than 10%.
引文
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12 Miao W,Yin Y,Nie C,et al.Surface recombination effects on aero-heating of high enthalpy flows.In:21st AIAA International Space Planes and Hypersonics Technologies Conference.Xiamen,2017
13 Norman P,Schwartzentruber T,Cozmuta I.Modeling Air-Si O2surface catalysis under hypersonic conditions with Reax FF molecular dynamics.In:10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference.Chicago,2010
14 陈连忠,程梅莎,洪文虎.Φ1 m电弧风洞大尺度防隔热组件烧蚀热结构试验.宇航材料工艺,2009,6:71–73
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16 高铁锁,董维中,江涛,等.化学模型对数值模拟等离子体流动的影响研究.宇航学报,2016,37:1193–1199
17 Votta R,Schettino A,Ranuzzi G,et al.Hypersonic low-density aerothermodynamics of orion-like exploration vehicle.J Spacecraft Rockets,2009,46:781–787
2 张志成,潘梅林,刘初平.高超声速气动热和热防护.北京:国防工业出版社,2003
3 卞荫贵,徐立功.气动热力学.合肥:中国科学技术大学出版社,2011.6
4孟松鹤,金华,王国林,等.热防护材料表面催化特性研究进展.航空学报,2014,35:287–302
5 苗文博,罗晓光,程晓丽,等.壁面催化对高超声速飞行器气动特性影响.空气动力学学报,2014,32:235–239
6 袁军娅,蔡国飙,杨红亮,等.高焓非平衡气动热环境的试验模拟及影响.试验流体力学,2012,26:35–39
7 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.航空学报,2015,36:311–324
8 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.空气动力学学报,2013,31:692–698
9 Muylaert J,Walpot L,Hauser J,et al.Standard model testing in the European High Enthalpy Facility F4 and extrapolation to flight.In:28th Joint Propulsion Conference and Exhibit,Joint Propulsion Conferences.Nashville,1992
10 许考,陈连忠.导管内塞式量热计热流测量实验及数值模拟研究.实验流体力学,2015,29:84–89
11 Thivet F,Pelissier C.Reduction of the hypersonic heat flux behavior on catalytic walls.In:12th AIAA International Space Planes and Hypersonic Systems and Technologies.Norfolk,2003
12 Miao W,Yin Y,Nie C,et al.Surface recombination effects on aero-heating of high enthalpy flows.In:21st AIAA International Space Planes and Hypersonics Technologies Conference.Xiamen,2017
13 Norman P,Schwartzentruber T,Cozmuta I.Modeling Air-Si O2surface catalysis under hypersonic conditions with Reax FF molecular dynamics.In:10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference.Chicago,2010
14 陈连忠,程梅莎,洪文虎.Φ1 m电弧风洞大尺度防隔热组件烧蚀热结构试验.宇航材料工艺,2009,6:71–73
15 董维中.热化学非平衡效应对高超声速流动影响的数值计算与分析.博士学位论文.北京:北京航空航天大学,1996
16 高铁锁,董维中,江涛,等.化学模型对数值模拟等离子体流动的影响研究.宇航学报,2016,37:1193–1199
17 Votta R,Schettino A,Ranuzzi G,et al.Hypersonic low-density aerothermodynamics of orion-like exploration vehicle.J Spacecraft Rockets,2009,46:781–787