The invention discloses a satellite structure for platform and load integration, which relates to the technical field of aerospace and solves the problems of large system mass, large size and the like caused by low resource utilization rate and high structure redundancy of an existing satellite structure system adopting a method that a platform and a load are separately designed. The satellite structure comprises an upper plate, a center bearing cylinder, side plates, a docking ring and a bottom plate, wherein the docking ring is used as an assembling reference, the bottom plate is installed on the docking ring, the center bearing cylinder is installed on the bottom plate, the upper plate is installed on the center bearing cylinder, the side plates are fixed on the side surfaces of the upper plate and the bottom plate, a plurality of upper plate brackets are uniformly arranged in the circumferential direction of the center bearing cylinder, and the upper plate is installed on the center bearing cylinder through the plurality of upper plate brackets. The satellite structure has the advantages of compactness, small size, light weight, high structure function density, high rigidity, large structure safety margin and high reliability.


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    Titel :

    Satellite structure for platform and load integration


    Beteiligte:
    GU SONG (Autor:in) / JIN GUANG (Autor:in) / ZHANG LEI (Autor:in) / AN YUAN (Autor:in) / GAO FEI (Autor:in) / XU ZHEN (Autor:in) / XU WEI (Autor:in)

    Erscheinungsdatum :

    27.05.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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