Liquid micro pulsed plasma thruster

被引：17

作者：

Szelecka, Agnieszka ^{[1
]}

Kurzyna, Jacek ^{[1
]}

Danilko, Dariusz ^{[1
]}

Barral, Serge ^{[2
]}

机构：

[1] IPPLM, PL-01497 Warsaw, Poland

[2] QuinteSci SERGE BARRAL, PL-00429 Warsaw, Poland

来源：

NUKLEONIKA | 2015年 / 60卷 / 02期

关键词：

electric propulsion; pulsed plasma thruster; liquid propellant;

D O I：

10.1515/nuka-2015-0057

中图分类号：

O61 [无机化学];

学科分类号：

070301 ; 081704 ;

摘要：

A new type of pulsed plasma thruster (PPT) for small satellite propulsion is investigated, of which the most innovative aspect is the use of a non-volatile liquid propellant. The thruster is based on an open capillary design. The thruster achieved a thrust-to-power ratio above 45 mu N/W, which constitutes a 5-fold improvement over the water-propelled pulsed plasma thruster, and which is also slightly above the performance of a similarly sized PPT with a solid propellant.

引用

页码：257 / 261

页数：5

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