A rocket fueling system (126) includes an insulated jacket (130) configured to removably couple to at least a portion of a rocket and form an enclosed space (152) between the insulated jacket (130) and the at least the portion of the rocket. The rocket fueling system (126) also includes a cryogen inlet (138) in the insulated jacket (130). The cryogen inlet (138) is configured to receive a cryogen into an interior chamber (160) of the insulated jacket (130). The rocket fueling system (126) further includes a cryogen outlet (162) in the insulated jacket (130). The cryogen outlet (162) is configured to provide the cryogen from the interior chamber (160) in the insulated jacket (130) to the at least the portion of the rocket in the enclosed space (152). The rocket fueling system (126) still further includes a gas outlet (172) in the insulated jacket (130) configured to exhaust the cryogen from the enclosed space (152), and a flammable gas sensor (174) configured to detect a flammable gas at the gas outlet (172).


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    Titel :

    ROCKET FUELING SYSTEM AND METHOD OF FUELING A ROCKET


    Weitere Titelangaben:

    RAKETENBETANKUNGSSYSTEME UND VERFAHREN HIERFÜR
    PROCÉDÉ ET SYSTÈME D'ALIMENTATION DE CARBURANT D'UN MOTEUR FUSÉE


    Beteiligte:
    WATTS DANIEL A (Autor:in) / JENKINS DAVID S (Autor:in)

    Erscheinungsdatum :

    28.10.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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