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Development of a Micro-Multi-Plasmajet-Array Thruster

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Описание материала

Microfabrication of a 3×3 micro-plasmajet array with ultra-violet lasers and their thrust performance tests were conducted for nozzle elements with exit height of 0.5 mm and length of 0.5 mm. To evaluate thrust characteristics of the 3×3 arrayed plasmajet, thrust characteristics of the thruster were compared with those of the micro-single-nozzle plasmajet. It was shown that the thrust and specific impulse of the micro-plasmajet array were higher than those of the micro-single-nozzle plasmajet due to the multi-jet effect. The typical values of the thrust, specific impulse and averaged per nozzle element of the 3×3 micro-plasmajet array thruster operated at 6.5W with 1.25 mg/sec of propellant mass flow per nozzle element were 0.77 mN, 62 sec, respectively. In addition, observation of the micro-nozzle discharges was conducted, and a new thruster with extended nozzle structure for which each electrode element was electrically isolated from nearby elements was developed. A preliminary DSMC computation on internal and exhaust nozzle-flow characteristics of micro-nozzles of multi-nozzle array was conducted.

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)

Asanuma K., Funaki I., Hitomi R., Horisawa H., Kobayashi N.

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