Abstract: In many embodiments of the invention, a space-based data center includes orbital server modules configured to be deployed in space, each module including a communication subsystem for module-to-module communications to form a data center, tiles arranged in a planar array, where each tile has a layered structure including solar cells forming a layer across a first surface, thermal radiator panels forming a layer across a second surface, electronic components distributed laterally in a layer between the layer of solar cells and the layer of thermal radiator panels, where each electronic component receives power locally from solar cells and rejects heat to the thermal radiator panel beneath it, where a first subset of tiles are compute tiles in which the electronic components include one or more computing processors and memory, and where a second subset of tiles are support tiles in which the electronics components include network switches and energy storage.

Abstract: Systems and methods for elastically foldable structures are described. The high-strain composite thin-shell structures offer high stiffness to mass ratio and increased packaging efficiency, with the additional advantage that their deployment is aided by releasing the strain energy stored in the elastic folds in a controlled quasistatic manner.

Abstract: A device can be configured as an under-constrained deployable system. Such a system can use under-constrained deployable couplers. A device may include a second segment coupled to the first segment by a high strain structure, wherein the high strain structure is bent to store deployment energy in a stowed configuration. Releasing the stored deployment energy can allow an under-constrained deployable system to transition to an expanded configuration. A tensioning system can transition an under-constrained deployable system to a deployed configuration.

Abstract: A kinematic hinge with asymmetric pin hole is described. The pin hole includes two separated flat surfaces arranged at a relative angle to form a V-shape. The flat surfaces provide respective two kinematic contact points with a surface of a hinge pin arranged within the pin hole. A centerline of the V-shape is in a plane that is parallel to a plane of a hinge leaf associated with the asymmetric pin hole. A centerline of the V-shape is in a plane that intersects the plane of associated hinge leaf. The pin hole includes a teardrop shape provided by two arc segments joined by tangent line segments. Further included is a split V-block having two distant flat surfaces and corresponding rounded surfaces. The asymmetric pin hole is implemented in one or both hinge leaves of the kinematic hinge. The hinge pin is rigidly attached to one of the two hinge leaves.

Abstract: In many embodiments of the invention, a space-based data center includes orbital server modules configured to be deployed in space, each module including a communication subsystem for module-to-module communications to form a data center, tiles arranged in a planar array, where each tile has a layered structure including solar cells forming a layer across a first surface, thermal radiator panels forming a layer across a second surface, electronic components distributed laterally in a layer between the layer of solar cells and the layer of thermal radiator panels, where each electronic component receives power locally from solar cells and rejects heat to the thermal radiator panel beneath it, where a first subset of tiles are compute tiles in which the electronic components include one or more computing processors and memory, and where a second subset of tiles are support tiles in which the electronics components include network switches and energy storage.

Abstract: A device can be configured as an under-constrained deployable system. Such a system can use under-constrained deployable couplers. A device may include a second segment coupled to the first segment by a high strain structure, wherein the high strain structure is bent to store deployment energy in a stowed configuration. Releasing the stored deployment energy can allow an under-constrained deployable system to transition to an expanded configuration. A tensioning system can transition an under-constrained deployable system to a deployed configuration.

Abstract: A deployable reflectarray has a plurality of strips arranged in quadrants forming the reflectarray. The copper ground plane and the copper dipoles are supported by facesheets made of epoxy reinforced by quartz fibers. The copper ground plane is separated from the copper dipoles by S-shaped springs made of epoxy reinforced by quartz fibers, which allow folding and deployment of the reflectarray.

Abstract: A deployable reflectarray has a plurality of strips arranged in quadrants forming the reflectarray. The copper ground plane and the copper dipoles are supported by facesheets made of epoxy reinforced by quartz fibers. The copper ground plane is separated from the copper dipoles by S-shaped springs made of epoxy reinforced by quartz fibers, which allow folding and deployment of the reflectarray.

Abstract: A deployable antenna is described. The antenna comprises a mesh attached to foldable ribs, a hub and a sub-reflector. The antenna can be stowed in a tight space for launching in space, and later deployed by extending out of its container. The antenna is designed to work in the Ka band or other bands and can increase data rates and function as a radio antenna.

Abstract: A deployable reflectarray antenna stowable in a 6U CubeSat volume is deployed through tape deployers and quartz cables. The telescoping waveguide is attached to the horn with a threaded insert. The reflectarray antenna has, at 37.75 GHz, a directivity of 48.5 dBi, a gain of 47.8 dBi, and an aperture efficiency of 42%. Hinges with a ball-end screw enable precise control of deployment angle of adjacent panels in the reflectarray antenna.

Abstract: A deployable antenna is described. The antenna comprises a mesh attached to foldable ribs, a hub and a sub-reflector. The antenna can be stowed in a tight space for launching in space, and later deployed by extending out of its container. The antenna is designed to work in the Ka band or other bands and can increase data rates and function as a radio antenna.

Abstract: A deployable reflectarray antenna stowable in a 6U CubeSat volume is deployed through tape deployers and quartz cables. The telescoping waveguide is attached to the horn with a threaded insert. The reflectarray antenna has, at 37.75 GHz, a directivity of 48.5 dBi, a gain of 47.8 dBi, and an aperture efficiency of 42%. Hinges with a ball-end screw enable precise control of deployment angle of adjacent panels in the reflectarray antenna.

Abstract: A reflectarray antenna comprises panels connected by rotating hinges. The panels are stowed folded around a satellite body and deploy by actuating the spring loaded hinges to extend and form a reflectarray for operation in the K/Ka or X-band. The feed deploys from the satellite body to allow formation of a high gain reflectarray antenna that occupies limited space in small satellite operations.

Abstract: A deployable antenna is described. The antenna comprises a mesh attached to foldable ribs, a hub and a sub-reflector. The antenna can be stowed in a tight space for launching in space, and later deployed by extending out of its container. The antenna is designed to work in the Ka band or other bands and can increase data rates and function as a radio antenna.