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首页> 外文期刊>Journal of propulsion and power >Plume characterization of electric solid propellant pulsed microthrusters
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Plume characterization of electric solid propellant pulsed microthrusters

机译：固体推进剂脉冲微推力器的羽流表征

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摘要

Electric solid propellants are an attractive option for propulsion because they are ignited only by an applied electric current. This leads to capabilities such as on-demand throttling and reignition in chemical combustion operation, and it lends itself to application in electric propulsion. In this work, the plasma plume created by electric solid propellant pulsed microthrusters is investigated using a nude Faraday probe, a triple Langmuir probe, and residual gas analysis. The thrusters are tested at a vacuum level of 2 × 10~(-5)torr. Results indicate an average plume electron temperature of 1.7 eV and a density of 10~(11) to 10~(14)cm~(-3). Atime-of-flight analysis indicates an exhaust velocity of 1500-1650 m/s on the centerline. Additionally, ionization fraction is estimated to be 0.3% for an ablation mass bit of 215 μg on average. Thermal equilibrium and adiabatic expansion calculations suggest a nonequilibrium gas with high-Temperature electrons and lower-Temperature neutral and ion species. Results indicate the pulsed microthruster operates similar to a coaxial pulsed plasma thruster, which is dominated by electrothermal effects.
机译：电固体推进剂是一种有吸引力的推进方式，因为它们只能通过施加的电流来点燃。这导致了诸如化学燃烧操作中的按需节流和重燃之类的功能，并且使其适合于在电推进中的应用。在这项工作中，使用裸法拉第探针，三重Langmuir探针和残留气体分析研究了由固体推进剂脉冲微推力器产生的等离子体羽流。推进器在2×10〜（-5）torr的真空度下进行测试。结果表明，平均羽状电子温度为1.7 eV，密度为10〜（11）至10〜（14）cm〜（-3）。飞行时间分析表明中心线上的排气速度为1500至1650 m / s。另外，对于平均215μg的烧蚀质量位，电离分数估计为0.3％。热平衡和绝热膨胀计算表明非平衡气体具有高温电子和低温中性和离子物质。结果表明，脉冲微推力器的运行方式与同轴脉冲等离子推力器类似，其主要受电热效应的影响。

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  • 来源
    《Journal of propulsion and power》 |2017年第4期|870-880|共11页
  • 作者

    Glascock Matthew S.; Rovey Joshua L.; Williams Shae E.; Thrasher Jason;

  • 作者单位

    Mechanical and Aerospace Engineering, Aerospace Plasma Laboratory, Missouri University of Science and Technology, 400 W. 13th Street., Rolla, MO, United States;

    Mechanical and Aerospace Engineering, Aerospace Plasma Laboratory, Missouri University of Science and Technology, 400 W. 13th Street., Rolla, MO, United States;

    Digital Solid State Propulsion, 5475 Louie Lane, Suite D, Reno, NV, United States;

    Digital Solid State Propulsion, 5475 Louie Lane, Suite D, Reno, NV, United States;

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