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.
RESISTOJET Propulsion System for Small Satellite
01.06.2019
1243158 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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