Study of the Design and Characteristics of a Modified Pulsed Plasma Thruster with Graphite and Tungsten Trigger Electrodes
Dosbolayev M. Igibayev Z. Ussenov Y. Suleimenova A. Aldabergenova T.
October 2025Multidisciplinary Digital Publishing Institute (MDPI)
Applied Sciences (Switzerland)
2025#15Issue 19
Featured Application: The application of plasma thrusters covers small spacecraft used in communication systems (including space-based Internet), image processing, scientific missions, and other projects. Such tasks require low-power, compact, cost-effective, and reliable propulsion systems. Solid-propellant pulsed plasma thrusters meet these requirements, offering scalability and the potential for miniaturization for nanosatellite applications. The paper presents experimental results for a modified pulsed plasma thruster (PPT) with solid propellant, using a coaxial anode–cathode design. Graphite from pencil leads served as propellant, and a tungsten trigger electrode was tested to reduce carbonization effects. Experiments were performed in a vacuum chamber at 0.001 Pa, employing diagnostics such as discharge current/voltage recording, power measurement, ballistic pendulum, time-of-flight (TOF) method, and a Faraday cup. Current and voltage waveforms matched an oscillatory RLC circuit with variable plasma channel resistance. Key discharge parameters were measured, including current pulse duration/amplitude and plasma channel formation/decay dynamics. Impulse bit values, obtained with a ballistic pendulum, reached up to 8.5 μN·s. Increasing trigger capacitor capacitance reduced thrust due to unstable “pre-plasma” formation and partial pre-discharge energy loss. Using TOF and Faraday cup diagnostics, plasma front velocity, ion current amplitude, current density, and ion concentration were determined. Tungsten electrodes produced lower charged particle concentrations than graphite but offered better adhesion resistance, minimal carbonization, and stable long-term performance. The findings support optimizing trigger electrode materials and PPT operating modes to extend lifetime and stabilize thrust output.
ballistic pendulum , Faraday cup , graphite electrode , pulsed plasma thruster , tungsten electrode
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Institute of Experimental and Theoretical Physics, Al-Farabi Kazakh National University, Almaty, 050040, Kazakhstan
Princeton Plasma Physics Laboratory, Princeton University, Princeton, 08543, NJ, United States
Institute of Nuclear Physics, Almaty, 050032, Kazakhstan
Institute of Experimental and Theoretical Physics
Princeton Plasma Physics Laboratory
Institute of Nuclear Physics
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