Diagnostics and performance of a low-power MPD thruster with appliedmagnetic nozzle
Diagnostics and performance of a low-power MPD thruster with appliedmagnetic nozzle
复制标题
具有应用磁力喷嘴的低功率 MPD 推进器的诊断和性能
DOI：
10.2514/3.23658
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发表时间：
1993
影响因子：
1.9
通讯作者：
G. Soulas
中科院分区：
文献类型：
--
作者：
T. York;C. Zakrzwski;G. Soulas
本研究评估了一台50-150kW推进器的性能，该推进器是台标磁浆动力(MPD)推进器的J级；它在有和没有外加磁喷嘴磁场的情况下运行。网络中的电容器(14 JnF)和电感(80/um)产生相对恒定的电流约450/us以产生所施加的磁喷嘴，并产生高达2.3kA的恒定电流约300/us以驱动推进器。采用实心铜电极时，由于实验持续时间较短，推力室不受外加磁场的影响。在m=0.135 g/S以下，I-Scale装置出现质量饥饿；这相当于2 g/S的足尺MPD推进器，当m>；0.25g/S时，装置运行平稳，有轻微的侵蚀。有无外加磁喷嘴磁场时的电流-电压记录相似，表明外加喷嘴对功率沉积的影响很小。在这个瞬变实验中，磁喷嘴的应用在轴向范围内减小了推力室外膨胀区的电流羽流。用局部压力探头测量排气流动中的动量通量。在相同的电弧功率下，施加磁喷嘴的冲击压力是自场作用下的3-4倍。此外，冲击压力随着推进器功率的增加而增加。对于1.15kA和2.30kA的情况，使用磁性喷嘴后，综合冲击压力的推力增加了1.6倍。使用朗缪尔探针测量了局部电子密度和温度；这些值与撞击压力一起被用来确定流速。对于1.15kA和2.30kA的情况，磁喷嘴的排气速度值分别提高了1.1和1.6倍。
This study evaluates the performance of a 50-150-kW thruster which was j-scale of a bench mark magnetoplasmadynamic (MPD) thruster; it was operated with and without applied magnetic nozzle fields. Capacitors (14 jnF) and inductors (80 /uH) in networks produced relatively constant currents for about 450 /us to generate the applied magnetic nozzle, and currents up to 2.3-kA constant for about 300 /us to drive the thruster. With the solid copper electrode, the applied magnetic field was excluded from the thrust chamber because of the short duration of the experiments. The i -scale device was mass starved below m = 0.135 g/s; this was equivalent to 2 g/s for a full-scale MPD thruster with the same ml A. With m > 0.25 g/s, the device was found to operate smoothly and with tittle evident erosion. Current-voltage records were similar with and without applied magnetic nozzle fields, indicating little effect of the external nozzles on the power deposition. The current plume in the expansion region outside the thruster chamber was reduced in axial extent with the application of the magnetic nozzle in this transient experiment. Momentum flux in the exhaust flow was measured by local pressure probes. For the same arc power, impact pressures with magnetic nozzles applied were 3-4 times larger than the self-field cases. Also, impact pressure increased with thruster power. For the 1.15and 2.30-kA cases, thrust from integrated impact pressure increased by a factor of 1.6 with magnetic nozzles applied. Local electron density and temperature were determined using Langmuir probes; these values along with impact pressure were used to determine flow velocity. For the 1.15and 2.30-kA cases, values of exhaust velocity increased by factors of 1.1 and 1.6, respectively, when the magnetic nozzles were applied.