Performance and Probe Measurements of a Radio-Frequency Plasma Thruster
Performance and Probe Measurements of a Radio-Frequency Plasma Thruster
复制标题
射频等离子推进器的性能和探头测量
DOI：
10.2514/1.b34720
复制
发表时间：
2013
影响因子：
1.9
通讯作者：
A. Gallimore
中科院分区：
文献类型：
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作者：
A. Shabshelowitz;A. Gallimore
利用密歇根大学大型真空试验装置中的位移式倒立摆推力台，对射频等离子体推进器的性能进行了评估。射频发生器以13.56兆赫的固定频率向射频等离子体推进器提供高达2000兆瓦的功率。匹配网络放置在推进器的真空室内，在匹配网络输入端口处使用双向耦合器测量射频功率。法拉第探头测量推进器远场排气中的电流密度，延迟电位分析仪表征离子电压分布，朗缪尔探头测量等离子体电位。射频等离子体推进器采用Ar推进剂，质量流量为2.4~7.6 mg/S，相应的修正装置压力为1.5×10−6~4.6×10−6 Torr。观测到的最大推力为10.8mN，最大比冲为303mN，推力效率在任何情况下均小于1%。
The performance of a radio-frequency plasma thruster is evaluated using a displacement-type, inverted-pendulum thrust stand in the Large Vacuum Test Facility at the University of Michigan. A radio-frequency generator supplies up to 2000 W to the radio-frequency plasma thruster at a fixed frequency of 13.56 MHz. The matching network is placed inside the vacuum chamber at the thruster, and the radio-frequency power is measured at the matching network input port with a dual-directional coupler. A Faraday probe measures the current density in the far-field exhaust of the thruster, a retarding potential analyzer characterizes the ion voltage distribution, and a Langmuir probe measures the plasma potential. The radio-frequency plasma thruster is operated with argon propellant at mass flow rates of 2.4–7.6 mg/s, at corresponding corrected facility pressures of 1.5×10−6–4.6×10−6 torr. The maximum thrust observed is 10.8 mN, and the maximum specific impulse is 303 s. Thrust efficiency is below 1% at all conditio...
航天器推进系统陶瓷推进器的研制
DOI：
--
发表时间：
2004
期刊：
4^<th> International Spacecraft Propulsion Conference 2-9
影响因子：
--
作者：
K.Takita;K.Hisatsune;Y.Nonaka;H.Mishima;K.T.Uesugi;E.Sato;S.Sawai
通讯作者：
S.Sawai