A small satellite propulsion system using a gaseous oxidizer and a gaseous fuel as primary propellants with a liquid as a film coolant for the inner surface of the rocket motor. The gaseous fuel is also used as a pressurant for the coolant and as a cold gas propellant for attitude control system (hereinafter “ACS”) thrusters. The oxidizer, fuel, and coolant tanks, as well as most valves and plumbing, are integrated into a single core unit along with the rocket motor, rocket motor plumbing, and safety valves. Attitude control thrusters may be remotely located with plumbing to the fuel tank. The core unit is four inches high and less than four inches deep and wide. The small satellite propulsion system uses no pyrotechnics and no hazardous toxic materials.


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    Titel :

    Small satellite propulsion system


    Beteiligte:

    Erscheinungsdatum :

    09.03.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    SMALL SATELLITE PROPULSION SYSTEM

    DROPPERS LLOYD J | Europäisches Patentamt | 2016

    Freier Zugriff

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    Small Satellite Propulsion Options

    Myers, R. M. / Oleson, S. R. / Curran, F. M. et al. | British Library Conference Proceedings | 1994


    Small Satellite Propulsion Options

    R. M. Myers / S. R. Oleson / F. M. Curran et al. | NTIS | 1994