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.

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.

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 $·$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.

The purpose of this work is to study the dependence of thrust-power characteristics and electrode geometry of a solid-fueled pulse-plasma engine (PPE) was carried out in a series of experiments. The results of the study revealed useful dependences that reveal the relationship between the capacitor capacity and the pulse bit of the PPE, as well as between the geometry of the electrodes and the thrust characteristics of the PPE. According to the obtained data the following conclusions can be made, with increasing the capacitor capacitance from 3μF to 5μF contributes to improving the traction characteristics, while reducing the distance between the electrodes by changing the anode diameter from 6mm to 10mm negatively affects the traction characteristics of a PPE. These dependencies were obtained by changing the voltage between the coaxial electrodes from 2kV to 3.5kV in 0.5kV increments. They play an important role in further improvement and optimization of the solid-propellant PPE design, as well as to ensure their effective operation in space conditions. The results obtained are valuable information for designers and engineers working in the field of space technology. They can be used in further research and development aimed at creating more efficient and reliable solid-propellant PPEs that can successfully perform the tasks of orbit correction and maintaining the stable position of small spacecraft. This opens new prospects for the development of space engineering and ensuring more efficient use of solid propellant in plasma engines. Целю данной работы, являются изучения зависимости тягово-энергетических характеристик и геометрии электродов импульсно-плазменного двигателя (ИПД) с твердым топливом была проведена серия экспериментов. Результаты исследования позволили выявить полезные зависимости, которые раскрывают связь между емкостью конденсатора и импульсом бита ИПД, а также между геометрией электродов и тяговыми характеристиками ИПД. По полученным данным можно сделать следующие выводы, с увеличение емкости конденсаторов с 3мкФ на 5мкФ способствует улучшению тяговых характеристик, в то время как уменьшение расстояния между электродами посредством изменения диаметра анода с 6мм на 10мм отрицательно влияет на тяговые характеристики ИПД. Эти зависимости были получены при изменении напряжения между коаксиальных электродов с 2кВ до 3,5кВ с шагом 0,5кВ. Они играют важную роль в дальнейшем улучшении и оптимизации конструкции твердотопливных ИПД, а также позволяют обеспечить их эффективное функционирование в условиях космического пространства. Полученные результаты представляют собой ценную информацию для разработчиков и инженеров, работающих в области космической технологии. Они могут быть использованы в дальнейших исследованиях и разработках, направленных на создание более эффективных и надежных твердотопливных ИПД, способных успешно выполнять задачи корректировки орбиты и поддержания стабильного положения малых космических аппаратов. Это открывает новые перспективы для развития космической инженерии и обеспечения более эффективного использования твердого топлива в плазменных двигателях. Бұл жұмыстың мақсаты қатты отынмен импульстік-плазмалық қозғалтқыштың (ИПҚ) тартқыш-энергетикалық сипаттамалары мен электродтарының геометриясына тәуелділікті зерттеу болып табылады. Зерттеу нәтижелері конденсатордың сыйымдылығы мен ИПҚ бит импульсі арасындағы, сондай-ақ электродтардың геометриясы мен ИПҚ тарту сипаттамалары арасындағы байланысты ашатын пайдалы тәуелділіктерді анықтау. Алынған мәліметтерге сәйкес келесі тұжырымдар жасауға болады, конденсаторлардың сыйымдылығын 3 мкФ-тан 5 мкФ-қа дейін арттырған кезде, тарту сипаттамалары арттады, ал анодтың диаметрін 6 мм-ден 10 мм-ге өзгерту арқылы электродтар арасындағы ара қашықтықты азайту ИПҚ -тың тарту сипаттамаларыңа кері әсер етеді. Бұл тәуелділіктер коаксиалды электродтар арасындағы кернеу 0,5 кВ қадаммен 2 кВ-тан 3,5 кВ-қа дейін өзгерген...

В этом исследовании были проведены некоторые эксперименты в целях оптимизации процесса поджига и его влияния на формирование и развитие основного плазменного потока. Искра поджига возникает при соприкосновении графитового стержня с заземленным электродом. С другой стороны графитовый электрод используется в качестве топлива в импульсном плазменном двигателе (ИПД). Динамика формирования импульсного разряда зафиксирована с использованием высокоскоростной камеры CMOS Phantom VEO710S, что позволило зарегистрировать ключевые стадии возникновения и ускорения плазмы. Эмиссионный спектр разряда был получен с помощью линейного спектрометра Optosky, что дало возможность провести анализ состава плазмы и определить источник тяги. Изменение силы тока искрового и основного разрядов во времени было измерено с использованием пояса Роговского.