RESISTOJET propulsion system for small satellite

被引：4
|
作者：
Djamal, Darfilal [1 ]
Mohamed, Khatir [2 ]
Aslan, Alim Rustem [3 ]
机构：
[1] Satellites Dev Ctr CDS, Satellites Engn Dept, Oran, Algeria
[2] Algerian Space AgencyASAL, Algiers, Algeria
[3] ITU Fac Aeronaut & Astronaut, Istanbul, Turkey
来源：
2019 9TH INTERNATIONAL CONFERENCE ON RECENT ADVANCES IN SPACE TECHNOLOGIES (RAST) | 2019年
关键词：
RESISTOJET; Cold gas; small satellites; heater;
D O I：
10.1109/rast.2019.8767847
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Due to the launch safety constraints placed on Space companies built microsatellites, designing a simple and reliable propulsion system with performance and characteristics in line with the typical requirements of microsatellites presents a significant challenge to aspiring engineers. This paper presents the design process of a low-cost, propulsion system with a two-phase high density propellant. The aim of this study is the preliminary design of a 50mN RESISTOJET system operating at low pressure. The preliminary design and the optimization of the thruster dimensions are presented.
引用
收藏
页码：159 / 166
页数：8
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