Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.


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    Titel :

    Electrically operated propellant for solid rocket motor thrust management


    Beteiligte:

    Erscheinungsdatum :

    18.02.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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





    SOLID PROPELLANT ROCKET MOTOR

    W. L. Dowler / J. I. Shafer / J. W. Behm et al. | NTIS | 1971


    Solid Propellant Rocket Motor

    W. L. Dowler / J. I. Shafer / J. W. Behm et al. | NTIS | 1973


    Solid propellant rocket motor

    Dowler, W. L. / Shafer, J. I. / Behm, J. W. et al. | NTRS | 1973