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.


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    Titel :

    RESISTOJET Propulsion System for Small Satellite


    Beteiligte:


    Erscheinungsdatum :

    2019-06-01


    Format / Umfang :

    1243158 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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