Research and Development of Electrothermal Pulsed Plasma Thruster Systems Onboard the Osaka Institute of Technology 2nd PROITERES Nano-Satellite

Fujita, Ryota; Kanaoka, Keita; Ono, Kohei; Morikawa, Naoki; Ryuho, Koki; Enomoto, Kosuke; Tahara, Hirokazu; Takada, Kyoko; Wakizono, Takashi

doi:10.2322/jjsass.66.91

Cited by 2 publications

References 6 publications

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Influence of the discharge circuit inductance on the ablative pulsed plasma thruster performance

Diakonov

Lyubinskaya

Semenikhin

2020

IOP Conf. Ser.: Mater. Sci. Eng.

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The most promising option for motion control of small spacecrafts with weight less than 50 kg is a pulsed plasma thruster with an energy of less than 20 J (micro-PPT), which has such advantages as low weight, structure simplicity, precise pulse control, sufficiently long life time, constant operational readiness and low inertia. It was believed that PPT with low discharge energy (less than 20 J) needed reduction of the initial inductance, despite the fact that the low capacity of the capacitor bank would not allow to achieve the optimal C/Lo ratio. However, the results of calculations and experiments show that a slight increase in the initial inductance of the discharge circuit, contrary to the assumptions, has a positive effect on the micro-PPT characteristics, reducing the propellant consumption and mainly increasing the specific impulse without significant reduction of the thrust impulse (unit impulse). This feature of the discharge circuit of the PPT with a low discharge energy allows us to discover new solutions in micro-PPT designing and improve the thruster specific characteristics.

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Influence of the discharge circuit inductance on the ablative pulsed plasma thruster performance

Diakonov

Lyubinskaya

Semenikhin

2020

IOP Conf. Ser.: Mater. Sci. Eng.

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R&D, Launch and Initial Operation of the Osaka Institute of Technology 1st PROITERES Nano-Satellite with Electrothermal Pulsed Plasma Thrusters and Development of the 2nd and 3rd Satellites

Egami

Matsuoka

Sakamoto

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The Project of Osaka Institute of Technology Electric-Rocket-Engine onboard Small Space Ship (PROITERES) was started at Osaka Institute of Technology in 2007. In PROITERES, a nano satellite named the 1st PROITERES satellite with electrothermal pulsed plasma thrusters (PPTs) was launched by Indian PSLV C-21 rocket on September 9, 2012. We developed Bread Board Model (BBM) and Engineering Model (EM) of the satellite, including electrothermal PPT system, high-resolution camera system, onboard-computer system, communication system and ground station, electric power system, attitude control system etc, in 2007-2009. Finally, the development of the satellite Flight-Model (FM) was completely finished in 2010. In this paper, we introduce the R&D feature and final checking, launch process and initial operation of the satellite FM including EP system. Furthermore, the research and development of the 2nd and 3rd PROITERES satellites with high-power electric thrusters, i.e., high-power electrothermal PPT and cylindrical Hall thruster are also introduced.

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Research and Development of Electrothermal Pulsed Plasma Thruster Systems Onboard the Osaka Institute of Technology 2nd PROITERES Nano-Satellite

Cited by 2 publications

References 6 publications

Influence of the discharge circuit inductance on the ablative pulsed plasma thruster performance

Influence of the discharge circuit inductance on the ablative pulsed plasma thruster performance

R&D, Launch and Initial Operation of the Osaka Institute of Technology 1st PROITERES Nano-Satellite with Electrothermal Pulsed Plasma Thrusters and Development of the 2nd and 3rd Satellites

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