平面感应式脉冲等离子体推力器高速脉冲气体供给阀的试验验证
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摘要
本文针对国防科技大学的平面感应脉冲等离子体推力器(IPPT)原型机,设计了一种基于感应涡流斥力原理的快速脉冲气体供给阀.该阀采用截锥型铍青铜簧片作为执行构件,依靠簧片开启过程中弹性变形产生的弹力提供闭合所需回复力,避免了使用额外的回复力机构,使阀整体结构得到极大简化.性能测试结果表明,该阀的动作延迟时间小于35μs.在阀腔气体压力为100 k Pa时,最大单脉冲供气量为2.5 mg.响应特性和供气量特性均满足目前IPPT原型机的需求.此外,该阀可通过调节初始充电电压和阀腔气体压力实现供气量调节.该阀可以为后续推力器原型机多工况性能试验提供有力支持.
A prototype inductive pulsed plasma thruster( IPPT) has been developed in the National University of Defense Technology. In order to support the thruster experimental research,a novel fast pulsed gas valve based on eddy current repulsion mechanism is designed and tested in this paper. A new and important design feature is the use of a conical diaphragm as the action part,which greatly contributes to the virtue of simplicity for adopting the resultant force of the diaphragm deformation as the closing force. Experiments are performed over a range of capacitor charge voltages and working gas pressures,and the results reveal that the delay before the valve action is less than 35 μs. The throughput of the valve,which has an upper limit of 2. 5 mg argon with a fixed gas pressure of 100 k Pa,can be easily regulated by adjusting the charge voltage and the gas pressure. The valve will become a useful tool to facilitate the IPPT research.
A prototype inductive pulsed plasma thruster( IPPT) has been developed in the National University of Defense Technology. In order to support the thruster experimental research,a novel fast pulsed gas valve based on eddy current repulsion mechanism is designed and tested in this paper. A new and important design feature is the use of a conical diaphragm as the action part,which greatly contributes to the virtue of simplicity for adopting the resultant force of the diaphragm deformation as the closing force. Experiments are performed over a range of capacitor charge voltages and working gas pressures,and the results reveal that the delay before the valve action is less than 35 μs. The throughput of the valve,which has an upper limit of 2. 5 mg argon with a fixed gas pressure of 100 k Pa,can be easily regulated by adjusting the charge voltage and the gas pressure. The valve will become a useful tool to facilitate the IPPT research.
引文
[1]POLZIN K A.Comprehensive review of planar pulsed inductive plasma thruster research and technology[J].Journal of Propulsion and Power,2011,27(3):513-531.
[2]程谋森,李小康,车碧轩,等.感应式脉冲等离子体推力器技术研究综述[J].空间控制技术与应用,2017,43(5):1-6.CHENG M S,LI X K,CHE B X,et al.Review of technology and research on inductive pulsed plasma thruster[J].Aerospace Control and Application,2017,43(5):1-6.
[3]DAILEY C L,LOVBERG R H.The PITMk V pulsed inductive thruster[D].NASA-CR-191155,1993.
[4]RUSSELL D,POYLIO J H,GOLDSTEIN W,et al.The Mark VIpulsed inductive thruster[C]∥Space Conference and Exhibit.San Diego,California:AIAA2004-6054,2004.
[5]DAILEY C L,LOVBERG R H.Pulsed inductive thruster component technology[D].AD-A181068,1987.
[6]POYLIO J H,RUSSELL D,GOLDSTEIN W,et al.Pulsed inductive thruster:flight-scale proof of concept demonstrator[C]∥40thAIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Fort Lauderdale,Florida:AIAA2004-3640,2004.
[7]DAILEY C L.Thrust measurement for a pulsed inductivethrusters[D].AD702498,1970.
[8]DAILEY C L,LOVBERG R H.Pulsed electromagnetic thruster[D].AD735721,1971.
[9]DAILEY C L,LOVBERG R H.Pulsed inductive thruster development[D].AD-A094884,1979.
[10]郭大伟,程谋森,杨雄,等.高速重复脉冲式径向流动微量气体供给阀:中国,ZL201610413918.8[P].2017.11.28.GUO D W,MOU S C,YANG X,et al.Fast repetitive pulsed gas valve withtoroidal orifice:China,ZL201610413918.8[P].2017.11.28.
[11]刘玉魁.真空工程设计[M].北京:化学工业出版社,2016:737-738.LIU Y K.Design of vacuum engineering[M].Beijing:Chemical Industry Press,2016:737-738.
[12]徐华舫.空气动力学基础(下册)[M].北京:北京航空学院出版社,1987:7,19.XU H F.Fundamentals of aerodynamics(Volume two)[M].Beijing:Beijing University of Aeronautics and Astronautics Press,1987:7,19.
[2]程谋森,李小康,车碧轩,等.感应式脉冲等离子体推力器技术研究综述[J].空间控制技术与应用,2017,43(5):1-6.CHENG M S,LI X K,CHE B X,et al.Review of technology and research on inductive pulsed plasma thruster[J].Aerospace Control and Application,2017,43(5):1-6.
[3]DAILEY C L,LOVBERG R H.The PITMk V pulsed inductive thruster[D].NASA-CR-191155,1993.
[4]RUSSELL D,POYLIO J H,GOLDSTEIN W,et al.The Mark VIpulsed inductive thruster[C]∥Space Conference and Exhibit.San Diego,California:AIAA2004-6054,2004.
[5]DAILEY C L,LOVBERG R H.Pulsed inductive thruster component technology[D].AD-A181068,1987.
[6]POYLIO J H,RUSSELL D,GOLDSTEIN W,et al.Pulsed inductive thruster:flight-scale proof of concept demonstrator[C]∥40thAIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Fort Lauderdale,Florida:AIAA2004-3640,2004.
[7]DAILEY C L.Thrust measurement for a pulsed inductivethrusters[D].AD702498,1970.
[8]DAILEY C L,LOVBERG R H.Pulsed electromagnetic thruster[D].AD735721,1971.
[9]DAILEY C L,LOVBERG R H.Pulsed inductive thruster development[D].AD-A094884,1979.
[10]郭大伟,程谋森,杨雄,等.高速重复脉冲式径向流动微量气体供给阀:中国,ZL201610413918.8[P].2017.11.28.GUO D W,MOU S C,YANG X,et al.Fast repetitive pulsed gas valve withtoroidal orifice:China,ZL201610413918.8[P].2017.11.28.
[11]刘玉魁.真空工程设计[M].北京:化学工业出版社,2016:737-738.LIU Y K.Design of vacuum engineering[M].Beijing:Chemical Industry Press,2016:737-738.
[12]徐华舫.空气动力学基础(下册)[M].北京:北京航空学院出版社,1987:7,19.XU H F.Fundamentals of aerodynamics(Volume two)[M].Beijing:Beijing University of Aeronautics and Astronautics Press,1987:7,19.