HINGE-LOCKING MECHANISM FOR DEPLOYABLE SOLAR ARRAY
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United States of America
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Issued Date -
Apr 10, 2025
app pub date -
Oct 7, 2024
filing date -
Oct 7, 2024
priority date (Note) -
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status (Latency Note)
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Abstract
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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