Experimental Study of a Planar Solid-Propellant Pulsed Plasma Thruster Using Graphite
Dosbolayev M. Igibayev Z. Yertayev O.
January 2026Multidisciplinary Digital Publishing Institute (MDPI)
Aerospace
2026#13Issue 1
The study presents an upgraded design and the results of experimental investigations of a solid-propellant pulsed plasma thruster (PPT) in which graphite simultaneously serves as both the propellant and the ignition element. The proposed configuration comprises a planar parallel system of copper electrodes and a graphite initiating electrode equipped with an electromagnetic discharge-triggering mechanism. Experimental tests were conducted under vacuum conditions of approximately 10−5 Torr at an energy-storage capacitor voltage of 800–1400 V. Discharge current amplitudes of up to 3.16 kA were recorded at a single-pulse energy of up to 4.41 J. The measured impulse bit was about 17.1 μN (Formula presented.) s, and the plasma jet exhaust velocity reached 11.1 km/s. Spectroscopic analysis of the plasma confirmed the presence of characteristic carbon emission lines, thereby indicating the active participation of the graphite propellant in the formation of the plasma plume. The present work continues previous research on PPTs with graphite electrodes and is aimed at further miniaturization of the earlier developed design. The primary objective of the study is the experimental validation of the proposed discharge concept in a planar parallel electrode configuration while preserving the key thrust and energy performance characteristics of the thruster.
graphite , impulse bit , pulsed plasma thruster , small spacecraft , solid propellant , spectroscopy , vacuum testing
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Institute of Experimental and Theoretical Physics, Al-Farabi Kazakh National University, Almaty, 050040, Kazakhstan
National Nanotechnology Open Laboratory, Al-Farabi Kazakh National University, Almaty, 050040, Kazakhstan
Institute of Experimental and Theoretical Physics
National Nanotechnology Open Laboratory
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