Artificial satellites are dependent on solar arrays to produce the power needed to support the functional components of the satellite. The present invention is directed to a hinge-locking mechanism designed to maximize the photovoltaic real estate of a solar array of an artificial satellite. The hinge-locking mechanism facilitates the deployment of the solar array upon the artificial satellite entering orbit. The hinge-locking mechanism utilizes a tapered pin with an internal spring resting against an asymmetrically oval shaped cam of a common pivot point. The hinge-lock trades kinetic energy of a solar panel for spring compression to permanently lock the solar array in place upon deployment while reducing the shock load and maximizing deployed stiffness.


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    Title :

    HINGE-LOCKING MECHANISM FOR DEPLOYABLE SOLAR ARRAY


    Contributors:
    RISKAS BRIAN (author) / VAN BRANDON (author)

    Publication date :

    2025-04-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    H02S GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRA-RED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, E.G. USING PHOTOVOLTAIC [PV] MODULES , Erzeugung elektrischer Energie durch Umwandlung von Infrarot-Strahlung, sichtbarem Licht oder ultraviolettem Licht, z.B. unter Verwendung von Photovoltaik [PV]-Modulen / B64G Raumfahrt , COSMONAUTICS



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