A small thruster, that will herein be called the Hydrazine milliNewton Thruster (HmNT), has been designed and vacuum hot-fire tested, demonstrating a range of thrust and impulse far below the current state-of-the-art (SOA) hydrazine thruster. Steady-state thrust levels of 35–135 mN, and minimum impulse-bits of 25–120 μN-s were demonstrated over a typical operating range of inlet pressures. These capabilities provide new spacecraft and mission design options, including the following: Functional backup for Reaction Wheel Assemblies (RWAs), which can be used to prolong the useful life of RWAs; RWA replacement for certain missions to save mass, power, and cost; Precision delta-V that can be used for: proximity operations and docking maneuvers, formation flying, primary attitude control for SmallSats and CubeSats, and primary delta-V for CubeSats.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    A Micro Newton Impulse-Bit Hydrazine Thruster - Design, Test, and Mission Applications


    Beteiligte:
    Scharf, Daniel P. (Autor:in) / Lewis, James R. (Autor:in) / Skulsky, David (Autor:in) / Blandino, John (Autor:in) / Parker, J. Morgan (Autor:in)

    Erscheinungsdatum :

    01.02.2018


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Micro-Newton Thruster Test Facility

    Hey, Franz Georg | Springer Verlag | 2018


    MICRO NEWTON COLLOID THRUSTER FOR ST7-DRS MISSION

    Gamero-Castano, M. / Hruby, V. / Spence, D. et al. | British Library Conference Proceedings | 2003



    Micro Newton Colloid Thruster System Development for ST7-DRS Mission

    Gamero-Castano, Manuel / Hruby, Vlad / Spence, Douglas et al. | AIAA | 2003