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Abstract <p>An approach is proposed to evaluating the thrust characteristics of ablative pulsed plasma thrusters (ablated mass, exhaust velocity, impulse bit, and thrust efficiency) based on an energy balance equation for such a system. The temperature in the thruster channel is estimated. A mathematical model is developed that enables prediction of the thruster’s operating regime by leveraging the magnetic to gas dynamic pressure ratio expressed in terms of the thruster’s structural parameters, including the ratio of inductances between the acceleration channel and external power circuit. An optimum inductance ratio that maximizes the impulse is found. The results of the evaluation made are consistent with the experimental data from the previous studies.</p>

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Technique for Estimating the Parameters of an Ablative Pulsed Plasma Thruster

  • 期刊论文

  • 发表日期：

    2025年8月1日

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  • D. A. Egoshin,
  • Yu. M. Grishin,
  • V. D. Telekh

摘要

Abstract

An approach is proposed to evaluating the thrust characteristics of ablative pulsed plasma thrusters (ablated mass, exhaust velocity, impulse bit, and thrust efficiency) based on an energy balance equation for such a system. The temperature in the thruster channel is estimated. A mathematical model is developed that enables prediction of the thruster’s operating regime by leveraging the magnetic to gas dynamic pressure ratio expressed in terms of the thruster’s structural parameters, including the ratio of inductances between the acceleration channel and external power circuit. An optimum inductance ratio that maximizes the impulse is found. The results of the evaluation made are consistent with the experimental data from the previous studies.