The present invention relates to a space launch vehicle for transporting a load from the earth to a space orbit or to space and, more specifically, to a carbon composite ultralight space launch vehicle fuselage manufactured using a carbon fiber reinforced composite for the fuselage of the launch vehicle and a propellant tank accommodated in the fuselage, and a manufacturing method thereof.

    La présente invention concerne un lanceur spatial pour transporter une charge de la Terre vers une orbite spatiale ou vers l'espace et, plus spécifiquement, un fuselage de lanceur spatial ultraléger en composite de carbone fabriqué à l'aide d'un composite renforcé par des fibres de carbone pour le fuselage du lanceur et un réservoir d'agent propulsif logé dans le fuselage, et son procédé de fabrication.

    본 발명은 지상에서 우주궤도 또는 우주공간까지 탑재물을 운송하기 위한 우주발사체에 관한 것으로, 더욱 상세하게는 우주발사체의 동체와 동체 내부에 수용되는 추진제 탱크를 탄소섬유 강화 복합재를 이용하여 제작하는 탄소복합재 초경량 우주발사체 동체 및 그 제조 방법에 관한 것이다.


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    Titel :

    ULTRALIGHT SPACE LAUNCH VEHICLE FUSELAGE AND MANUFACTURING METHOD THEREOF


    Weitere Titelangaben:

    FUSELAGE DE LANCEUR SPATIAL ULTRALÉGER ET SON PROCÉDÉ DE FABRICATION
    초경량 우주발사체 동체 및 그 제조 방법


    Beteiligte:
    HWANG DAEHYUN (Autor:in) / YOUK SANGWOO (Autor:in) / SHIN DONG YOON (Autor:in)

    Erscheinungsdatum :

    06.03.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Koreanisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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