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Thrust Performance and Cathode Temperature Evaluation of MW Class Quasi-Steady MPD Thruster

机译：兆瓦级准MPD推进器的推力性能和阴极温度评估

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Magnetoplasmadynamic (MPD) thruster is a candidate of next generation electric propulsion system for a mission that high thrust is required. We are developing the high power Self-field MPD arcjet of several hundred kW class using a numerical and thermal design tool. We are testing quasi-steady MPD thrusters as the validation tool for numerical tool. In order to validate the numerical simulation or the predict of sheath effect, the electrode temperature measurement is necessary owing to a great impact on the numerical simulation. This paper reports the cathode temperature measurement of the quasi-steady state MPD thruster with argon propellant in 160-1940 kW range and the cathode temperature using the 2-color pyrometer that we recently developed. The cathode tip temperature is near 3000 K above 13 kA. We reveals the temperature distribution heating only the cathode tip peculiar to the quasi-steady state experiment in lower the theoretical critical current. In addition, the cathode temperature change is clarified of 1 ms quasi-steady operation.
机译：磁等离子体动力（MPD）推进器是下一代电动推进系统的候选者，用于需要高推力的任务。我们正在使用数值和热设计工具开发几百千瓦级的大功率自磁场MPD电弧喷射器。我们正在测试准稳态MPD推进器，作为数值工具的验证工具。为了验证数值模拟或预测鞘效应，由于对数值模拟的影响很大，因此必须进行电极温度测量。本文报道了使用最近开发的2色高温计测量的准稳态MPD推进器在160-1940 kW范围内的阴极温度，以及阴极温度。阴极尖端温度在13 kA以上接近3000K。我们揭示了在较低的理论临界电流下仅加热准稳态实验所特有的阴极尖端的温度分布。另外，澄清了1 ms准稳态运行的阴极温度变化。

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