パルス型プラズマスラスタの二段階放電動作

概要

論文の詳細を見る
Double discharge operation for a pulsed plasma thruster (PPT) was proposed and the preliminary experiments were conducted to improve the lower propellant utilization efficiency of PPTs that is attributable mainly to a late-time vaporization problem. In the double discharge operation, two successive discharges were produced with a microseconds-order interval to accelerate the late-time vaporization gas generated in a primary discharge by the electromagnetic interaction in a secondary one. Experimental results showed by adopting the double discharge operation the effective exhaust velocity was increased compared with the one in the ordinary PPT operation. This velocity increment indicated that the ratio of electromagnetically accelerated propellant gas to total propellant consumption was risen in the double discharge operation. Furthermore, when the time interval between the two discharges was shorter than the single discharge duration, it was observed that the impulse bit, specific impulse and thruster efficiency were higher than those in the ordinary operation.
社団法人日本航空宇宙学会の論文
2003-03-05