Abstract An innovative concept for a rocket type thruster that can be beneficial for spacecraft trajectory corrections and station keeping was investigated both experimentally and theoretically. It may also be useful for divert and attitude control systems (DACS). The thruster is based on a combustion chamber discharging a weight through an exhaust tube. Calculations with granular double-base propellant and a solid ejected weight reveal that a specific impulse based on the propellant mass of well above 400s can be obtained. An experimental thruster was built in order to demonstrate the new idea and validate the model. The thruster impulse was measured both directly with a load cell and indirectly by using a pressure transducer and high speed photography of the weight as it exits the tube, with both ways producing very similar total impulse measurement. The good correspondence between the computations and the measured data validates the model as a useful tool for studying and designing such a thruster.

    Highlights An innovative concept of a rocket type thruster. Based on a combustion chamber ejecting a weight through an ejection tube. Can generate higher specific impulse than a standard rocket motor configuration. The thruster is investigated both experimentally and theoretically. Beneficial for spacecraft maneuvers and divert and attitude control systems.


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    Titel :

    Theoretical and experimental study of a thruster discharging a weight


    Beteiligte:
    Michaels, Dan (Autor:in) / Gany, Alon (Autor:in)

    Erschienen in:

    Acta Astronautica ; 99 ; 252-262


    Erscheinungsdatum :

    2014-01-29


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






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