A composite tank (100) for a reusable launch vehicle (101) comprises a composite wall (104), having a first coefficient of thermal expansion. The composite wall (104) comprises a first end (102), a second end (103), a central axis (106), which passes through the first end (102) and through the second end (103), and a cylindrical interior surface (105). The composite tank (100) also comprises slosh baffles (110), formed from a second material, having a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. Each of the slosh baffles (110) is attached to the cylindrical interior surface (105) of the composite wall (104). Each of the slosh baffles (110) is annular and is separated from the cylindrical interior surface (105) of the composite wall (104) by a radial gap (109), selected, in part, based on a difference between the first coefficient of thermal expansion and the second coefficient of thermal expansion. The radial gap (109) is configured to change responsive to changes in temperature of the composite tank (100).


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    Titel :

    COMPOSITE TANKS FOR REUSABLE LAUNCH VEHICLES AND METHOD OF FABRICATING THEREOF


    Weitere Titelangaben:

    VERBUNDTANKS FÜR WIEDERVERWENDBARE TRÄGERRAKETEN UND VERFAHREN ZU DEREN HERSTELLUNG
    RÉSERVOIRS COMPOSITES POUR VÉHICULES DE LANCEMENT RÉUTILISABLES ET SON PROCÉDÉ DE FABRICATION



    Erscheinungsdatum :

    2023-09-13


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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