The paper presents the appearance of a low-power electric propulsion system for a small remote sensing satellites based on an ablative pulsed plasma thruster. Preliminary analysis for the purpose and fields of application of ablative pulsed plasma thrusters (APPT) was carried out. The design appearance of a thruster for small remote sensing satellites was identified, and the main directions of APPT further development were defined. Methods for calculating the APPT propulsion characteristics were developed. The breadboard model of APPT for small remote sensing satellites was developed and made (APPT-350). Research tests of the breadboard model of APPT for Earth remote sensing small spacecrafts were carried out.

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This article describes the activities carried out by RIAME MAI in the field of low-power ion thrusters in 2010-2020. The results of study of a laboratory model of low power RIT using a different shape of GDC are presented. The results of work on creating an experimental model of such RIT with elements of the propulsion system are shown. The article also presents the research on the process of erosion of the accelerating electrode of the RIT - a critical element of the thruster design from the point of view of the lifetime.

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