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Evaluation of Pulsed Plasma Thruster Performance by Increase of Electric Power

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Описание материала

Research and development on pulsed plasma thruster (PPT) for small satellites have been conducting in Tokyo Metropolitan University. In this study, improvement of propulsive performance of coaxial PPT was conducted in order to apply it to propulsion systems for small satellite for not only attitude control but also orbit control or formation flight. As a result of changing the thruster dimension and input energy, total impulse of 266Ns and specific impulse of 490s was achieved with single propellant at continuous operation by 468,000 shots. In addition, in order to achieve a stable operation, the inductance of entire circuit was evaluated, and it confirmed that the energy density is one of the main parameters for the stable operation, but the dimensions and other configurations of the discharge chamber may affect that.

Характеристики

Дата проведения

September 11 – 15, 2011

Название конференции

32nd International Electric Propulsion Conference

место проведения

Wiesbaden Germany

Качество

excellent

Раздел

Аэрокосмическая техника

Язык

English

Типы файлов

pdf

Автор(ы)

Aoyagi J., Kitazono Y., Mimura D., Shindo T., Takegahara H., Umeda K.

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