用于驻点烧蚀试验的5kW等离子体发生器设计
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摘要
为了研究再入大气层时,飞行器所遭受的烧蚀情况和其外壳材料的热防护作用,围绕地面模拟再入环境的小型等离子体风洞系统,从等离子体发生器的功率计算和阴极、阳极结构参数入手,设计了用于驻点烧蚀试验的5kW级别小功率等离子体发生器。采用局域热力学平衡的方法,选择工作电流分别为90A,100A,110A和120A,对等离子体发生器性能的影响进行了研究。利用实验室真空系统与电源设备,开展初步点火试验,验证了等离子体发生器的基本性能。结果表明:与仿真计算结果相比,设计状态工质下的放电电压误差为8%,点火试验测得的放电电压误差为6.25%,参数对比验证了等离子体发生器仿真模型计算可靠,设计的等离子体发生器符合预期,工作正常。
In order to study the ablation of aircraft and the thermal protection of its shell materials when reentry into the atmosphere,a 5 kW level plasma generator was designed for the stagnation ablation test in small plasma wind tunnel based on the ground test of reentry. The power,cathode structure and anode structure of the plasma generator are analyzed and designed in detail. Adopting the magnetohydrodynamic model with the local thermodynamic equilibrium,the effects of current including 90A,100A,110A and 120A on the plasma generator were simulated and analyzed. A preliminary ignition test was carried out using laboratory vacuum system and power supply equipment to verify the basic performance of the plasma generator. The results show that,compared with the simulation results,the discharge voltage error of the designed working medium is 8%,and that of the ignition test is 6.25%. So the simulation model of plasma generator is reliable,the designed plasma generator meets the expectation and works normally. It provides an important reference for the subsequent stagnation ablation test.
In order to study the ablation of aircraft and the thermal protection of its shell materials when reentry into the atmosphere,a 5 kW level plasma generator was designed for the stagnation ablation test in small plasma wind tunnel based on the ground test of reentry. The power,cathode structure and anode structure of the plasma generator are analyzed and designed in detail. Adopting the magnetohydrodynamic model with the local thermodynamic equilibrium,the effects of current including 90A,100A,110A and 120A on the plasma generator were simulated and analyzed. A preliminary ignition test was carried out using laboratory vacuum system and power supply equipment to verify the basic performance of the plasma generator. The results show that,compared with the simulation results,the discharge voltage error of the designed working medium is 8%,and that of the ignition test is 6.25%. So the simulation model of plasma generator is reliable,the designed plasma generator meets the expectation and works normally. It provides an important reference for the subsequent stagnation ablation test.
引文
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[12]Butler G W,King D Q.Single and Two Fluid Simulations of ArcjetPerformance[R].AIAA 92-3104.
[13]王伟宗,荣命哲,Anthony B Murphy,等.高温氮气电弧等离子体物性参数的计算分析[J].高电压技术,2010,36(11):2777-2784.
[14]Megli T W,Krier H,Burton R L,et al.Two-Temperature Plasma Modeling of Nitrogen/Hydrogen Arcjets[J].Journal of Propulsion and Power,1996,12(6):1062-1069.
[15]Lago F,Gonzalez J J,Freton P,et al.A Numerical Modelling of an Electric Arc and Its Interaction with the Anode,Part I:The Two-Dimensional Model[J].Journal of Physics D Applied Physics,2004,37:883-897.
[2]Herdrich G,L?hle S,Auweter-Kurtz M,et al.IRSGround-Testing Facilities:Thermal Protection System Development,Code Validation and Flight Experiment Development[R].AIAA 2004-2596.
[3]Ozawa T,Suzuki T,Fujita K.Experimental and Numerical Studies of Hypersonic Flows in the Rarefied Wind Tunnel[R].AIAA 2010-4513.
[4]Burtner D,Keefer D,Ruyten W.Low-Power Ammonia Arcjet:Numerical Simulations and Laser-Induced Fluorescence Measurements[J].Journal of Propulsion and Power,1996,12(6):1123-1128.
[5]Butler G W,Kull A E,King D Q.Single Fluid Simulations of Low Power Hydrogen Arcjets[R].AIAA 1994-2870.
[6]黄河激,潘文霞,付志强,等.用于发动机热防护材料烧蚀实验的小型等离子体风洞[C].丽江:第一届高超声速科技学术会议,2008.
[7]王德文,杨月诚,查柏林.地面模拟再入烧蚀系统研究[J].测试技术学报,2013,27(3):248-253.
[8]廖宏图,吴铭岚,汪南豪.电弧喷射推力器内部工作过程研究综述[J].推进技术,1999,20(3):107-112.(LIAO Hong-tu,WU Ming-lan,WANG Nan-hao.Survey of Internal Process Studies on Arcjet Thrusters[J].Journal of Propulsion Technology,1999,20(3):107-112.)
[9]唐皇哉,赵文华,侯凌云,等.低功率电弧加热发动机的热效率[J].清华大学学报(自然科学版),2007,47(2):232-235.
[10]陈黎明.电弧加热发动机的设计与研究[D].北京:清华大学,2002.
[11]赵宇辉,王一白,代晓松,等.注氧位置对电弧加热等离子体发生器性能的影响[J].真空科学与技术学报,2017,(12):1177-1182.
[12]Butler G W,King D Q.Single and Two Fluid Simulations of ArcjetPerformance[R].AIAA 92-3104.
[13]王伟宗,荣命哲,Anthony B Murphy,等.高温氮气电弧等离子体物性参数的计算分析[J].高电压技术,2010,36(11):2777-2784.
[14]Megli T W,Krier H,Burton R L,et al.Two-Temperature Plasma Modeling of Nitrogen/Hydrogen Arcjets[J].Journal of Propulsion and Power,1996,12(6):1062-1069.
[15]Lago F,Gonzalez J J,Freton P,et al.A Numerical Modelling of an Electric Arc and Its Interaction with the Anode,Part I:The Two-Dimensional Model[J].Journal of Physics D Applied Physics,2004,37:883-897.