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<p>The simplicity, efficiency, and reliability of pulsed plasma thrusters make them a preferred choice in low-power systems for microsatellites. In this paper, a coaxial electrothermal pulsed plasma thruster was designed and tested using Teflon as a solid propellant. The ablated mass was measured for different values of peak discharge current and number of pulses. The Experimental results of our system were compared with calculated values obtained using a 1-D time-dependent ETFLOW model for the electrothermal capillary system. The model was used to calculate the values of thrust and impulse for each case. Experimentally, increasing the number of pulses resulted in an increase in the total ablated mass and the capillary diameter. Experimentally, increasing the peak discharge current from 1.95 kA to 5.66 kA led to an increase in the ablated mass per pulse from 128.4 µg to 980.8 µg and the impulse from 340 µN.s to 2156 µN.s. In addition, extending the capillary length from 3 to 8 cm led to an increase in the ablated mass from 52 µg to 326.2 µg, consistent with the calculated data. Moreover, the thrust efficiency was investigated as a function of input energy and capillary length. The maximum achieved thrust efficiency was about 8.9% for an input energy of 6 J and a capillary length of 6 cm. Theoretically, the model predicted that thrust, impulse, and specific impulse increase with raising the peak discharge current.</p>

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Investigation of a coaxial pulsed plasma thruster by electrothermal discharge in Teflon propellant

  • 期刊论文

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  • 发表日期：

    2025年6月25日

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  • M. M. Abo El-Hadeed,
  • M. E. Abdelkader,
  • F. B. Diab,
  • M. A. Abd Al-Halim

摘要

The simplicity, efficiency, and reliability of pulsed plasma thrusters make them a preferred choice in low-power systems for microsatellites. In this paper, a coaxial electrothermal pulsed plasma thruster was designed and tested using Teflon as a solid propellant. The ablated mass was measured for different values of peak discharge current and number of pulses. The Experimental results of our system were compared with calculated values obtained using a 1-D time-dependent ETFLOW model for the electrothermal capillary system. The model was used to calculate the values of thrust and impulse for each case. Experimentally, increasing the number of pulses resulted in an increase in the total ablated mass and the capillary diameter. Experimentally, increasing the peak discharge current from 1.95 kA to 5.66 kA led to an increase in the ablated mass per pulse from 128.4 µg to 980.8 µg and the impulse from 340 µN.s to 2156 µN.s. In addition, extending the capillary length from 3 to 8 cm led to an increase in the ablated mass from 52 µg to 326.2 µg, consistent with the calculated data. Moreover, the thrust efficiency was investigated as a function of input energy and capillary length. The maximum achieved thrust efficiency was about 8.9% for an input energy of 6 J and a capillary length of 6 cm. Theoretically, the model predicted that thrust, impulse, and specific impulse increase with raising the peak discharge current.