Abstract: The present invention is directed to a small, lightweight artificial satellite with edge computing capabilities. The artificial satellite is configured to perform onboard georectification and generation of analytics-ready data products. The artificial satellite includes at least one sensor operable to capture hyperspectral, multispectral, and/or video image data, and an onboard processor including at least one payload processor. The payload processor is operable to perform georectification and/or position rectification of image data using one or more onboard reference images, vector maps, positional data, and/or inter-satellite information, such that the image data is spatially accurate prior to transmission.

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.

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.

Abstract: The present invention is directed to a small, lightweight artificial satellite with edge computing capabilities. The artificial satellite includes a plurality of high-quality sensors to capture sensor data, which is then processed onboard the artificial satellite prior to transmitting the processed data. The artificial satellite of the present invention overcomes limitations of the prior art by reducing latency and enabling real-time data analytics through edge computing.

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.