Abstract: A hinged component fabrication method in which, in a layup stage of fabrication, the component includes a live hinge joining uncured material portions together at a hinge region and comprising a layer of tensile fabric at least partially infiltrated by an uncured elastomer layer at least partially interposed between the tensile fabric and the uncured material portions such that the uncured elastomer blocks the uncured material portions from infiltrating the hinge region. The method may include locating overlapped tensile fabric and elastomer layers in a tool and introducing polymer-based material into the tool such that polymer-based material portions overlap respective opposite ends of the fabric and elastomer layers. The polymer-based material portions are formed to a desired shape using the forming tool so that the fabric and elastomer layers form a live hinge between the polymer-based material portions.

Abstract: A head-mounted display (HMD) apparatus comprising at least one optical system, each optical system comprising a lens having a reflective optical surface and an HMD device associated with and distanced from the reflective optical surface. The HMD device comprises a substrate having horizontal and/or vertical convex curvatures having a curved geometric profile which continuously curves with smooth transitions in horizontal and/or vertical dimensions. The curved profile is dimensioned to curve around a temple of a wearer and extend in a direction toward an ear of a wearer. The substrate comprising a plurality of pixel elements arranged along the horizontal convex curvature and being controlled to selectively radiate light representative of computer-generated content (CGC) to the associated reflective optical surface such that those selected pixel elements for display emanate rays of the light for subsequent reflection from the reflective optical surface toward a respective one eye of the wearer.

Abstract: A pitch bearing assembly for a rotor blade and a hub assembly of a rotary wing aircraft includes a single inner race. An inboard outer race surrounds an inboard portion of the inner race and includes a first inboard blade connector and a second inboard blade connector that are configured to connect to the rotor blade. An inboard bearing is disposed between the inboard portion of the single inner race and the inboard outer race and includes an elastomer. An outboard outer race surrounds an outboard portion of the single inner race and includes a first outboard blade connector and a second outboard blade connector that are configured to connect to the rotor blade. An outboard bearing is disposed between the outboard portion of the inner race and the outboard outer race and includes an elastomer.

Abstract: Disclosed herein is a snap alignment guard for a nut plate ring. The alignment guard includes a curved elongated body comprising an inner surface and an outer surface. The alignment guard further includes a plurality of couplings extending from the inner surface. Each of the plurality of couplings are configured to engage a nut plate ring to attach the alignment guard to the nut plate ring. The elongated body forms a plurality of apertures defined in the outer surface. Each of the plurality of apertures are configured to receive at least a portion of a nut plate to maintain a circumferential position of the nut plate relative to an inner surface of the nut plate ring.

Abstract: In one embodiment, an aircraft includes a wing operable to fold along a wing fold gap. The wing comprises an inboard edge flap and an outboard edge flap, wherein the wing fold gap is between the inboard edge flap and the outboard edge flap. The aircraft further includes an input shaft operably coupled to the inboard edge flap, the input shaft mechanically coupled to a first magnetic torque coupler assembly at a first end of the input shaft. The wing further includes an output shaft operably coupled to the outboard edge flap, the output shaft mechanically coupled to a second magnetic torque coupler assembly at a first end of the output shaft. The first magnetic torque coupler assembly may magnetically couple to the second magnetic torque coupler assembly across the fold gap.

Abstract: An optical orbital angular momentum (OAM) encoding system includes an optical source configured to generate a source light, an optical OAM encoder configured to encode the source light based on OAM modes to generate an encoded light, and an optical unit configured to direct the encoded light to a target.

Abstract: In an embodiment, a system includes a three-dimensional (3D) printer, a neutral feedstock, a p-doped feedstock, an n-doped feedstock, and a laser. The 3D printer includes a platen and an enclosure. The platen includes an inert metal. The enclosure includes an inert atmosphere. The neutral feedstock is configured to be deposited onto the platen. The neutral feedstock includes a halogenated solution and a nanoparticle having a negative electron affinity. The p-doped feedstock is configured to be deposited onto the platen. The p-doped feedstock includes a boronated compound introduced to the neutral feedstock. The n-doped feedstock is configured to be deposited onto the platen. The n-doped feedstock includes a phosphorous compound introduced to the neutral feedstock. The laser is configured to induce the nanoparticle to emit solvated electrons into the halogenated solution to form, by reduction, layers of a ceramic comprising a neutral layer, a p-doped layer, and an n-doped layer.

Abstract: A modular spacecraft is provided. The modular spacecraft includes a bus module and a payload module. The bus module provides additional thermal radiative capacity for the payload module by including a bus-panel payload thermal zone that couples operational components of the payload module to a radiator panel in the bus module. The bus module also includes its own operational components that are thermally coupled to the radiator panel but that are thermally isolated from the payload module and the bus-panel payload thermal zone.

Abstract: In one embodiment, a fusion reactor includes an enclosure, one or more internal magnetic coils suspended within an interior of the enclosure and co-axial with a center axis of the enclosure, one or more encapsulating magnetic coils co-axial with the center axis of the enclosure, the encapsulating magnetic coils having a larger diameter than the internal magnetic coils, one or more mirror magnetic coils co-axial with the center axis of the enclosure, and one or more magnetic reconnection coils co-axial with the center axis of the enclosure, wherein the one or more magnetic reconnection coils, when pulsed by a power source, are disposed to reconfigure one or more magnetic fields within the enclosure. The reconfiguration, or magnetic reconnection, of the one or more magnetic fields is disposed to increase energy in the magnetic fields, thereby facilitating the conditions operable to generate plasma, and further, when the magnetic fields are collapsed, releasing the energy into the plasma.

Abstract: An optical system, apparatus, or method can comprise or implement a seed module to generate and output electromagnetic radiation at a predetermined amplitude and at a predetermined wavelength. The seed module can include at least one non-hollow core optical fiber and at least one hollow core optical fiber. One at least one non-hollow core optical fiber can be optically coupled to one at least one hollow core optical fiber. The non-hollow core optical fiber and the hollow core optical fiber may receive and pass electromagnetic radiation emitted from a laser diode or amplifier.

Abstract: The embodiments implement fraud-resistant biometric security based on polarization-based iris identification. The embodiments include identifying an iris based on unique patterns of polarized electromagnetic radiation (EMR) received from the iris.

Abstract: A switch comprising a first switching circuit assembly having a first pair of identical diodes in first anti-series configuration. The first switching circuit assembly constructed and arranged to cancel capacitance change wherein capacitance increases in a first diode of the first pair of identical diodes and, simultaneously, capacitance decreases in a second diode of the first pair of identical diodes with a first selectively applied radio frequency (RF) voltage input. The switch comprises a second switching circuit assembly having a second pair of identical diodes in second anti-series configuration. The second switching circuit assembly constructed and arranged to cancel capacitance change wherein capacitance increases in a first diode of the second pair of identical diodes and, simultaneously, capacitance decreases in a second diode of the second pair of identical diodes with a second selectively applied RF voltage input. A system and method are also provided.

Abstract: Systems, methods, and software described herein provide enhancements for the deployment and management of sensor resources across spaceborne, airborne, and ground-based physical nodes. In one implementation, a method includes collecting sensor data from physical sensors distributed over a geographic region, and establishing logical sensors based at least on requirements indicated by data requestors. The method includes allocating selected portions of the sensor data to the logical sensors to form composite sensor data based on locations monitored by the physical sensors that correspond to the requirements, and providing the composite data in one or more data streams to the data requestors as originating from the logical sensors.

Abstract: A nacelle for an engine includes an exterior housing a least partially surrounding the engine. The nacelle further includes a front portion proximate an engine face of the engine. The front portion of the nacelle defines an opening into an interior of the nacelle. The nacelle further includes a seal disposed proximate the opening. The seal is configured to selectively allow air into the interior of the nacelle. The nacelle further includes a heat exchanger disposed within the interior of the nacelle. The heat exchanger is configured to exchange heat between a fluid flowing within the heat exchanger and air at the interior of the nacelle.

Abstract: A dual-lenslet array photonic integrated circuit (PIC) imager includes a PIC and top and bottom substrate spacers. A first optical prism couples a first lenslet array to a first-side edge of the PIC. A second optical prism couples a second lenslet array to a second-side edge of the PIC. Lenslets of the first lenslet array and respective lenslets of the second lenslet array are coupled to respective waveguides embedded in the in the PIC.

Abstract: A cable can be used to facilitate electrical connections between electrical components. The cable can include a plurality of cable strands forming a void space. An adhesive paste can be applied within the void space. The adhesive paste can include a plurality of metallic nanoparticles. The metallic nanoparticles can fuse with each other and with the plurality of cable strands when energy is applied the connector and the cable. The metallic nanoparticles can include a surfactant, which can be displaced as pressure is applied. Heat can be applied to the adhesive paste to fuse the metallic nanoparticles.

Abstract: A satellite communication system includes a satellite, a satellite base station, and a user device. The satellite supports a number of satellite beams. Each satellite beam includes a number of cells. The satellite base station can communicate with the satellite via a feeder link. The user device is in communication with the satellite and the satellite base station. The user device can select a cell that covers a location of the user device based on a cell contour and a quality of a downlink signal received from the satellite base station. The satellite communication system can be operated by using LTE and/or NB-IoT standards, protocols, and/or waveforms.

Abstract: An instrumentation system for use with a component formed from a first material having non-uniform coefficients of thermal expansion includes a first sensing system configured to be mounted to the component to sense temperature and mechanical forces on the component, and a thermally compensating coupon configured to be mounted to the component adjacent the first sensing system. The thermally compensating coupon is formed from a second material having non-uniform coefficients of thermal expansion that are substantially identical to the non-uniform coefficients of thermal expansion of the first material. A thermally compensating sensing system is mounted to the thermally compensating coupon and connected to the first sensing system.

Abstract: A hybrid bearing system includes a self-lubricated bearing assembly including a self-lubricated bearing element and at least one elastomeric bearing assembly arranged adjacent the self-lubricated bearing assembly. The elastomeric bearing assembly is torsionally mated with the self-lubricated bearing element as a torsional load is applied about an axis of the self-lubricated bearing.

Abstract: A mounting system for functionally-coupling a line-replaceable unit with a structural manifold for supplying fluid coolant can comprise a fastener for the line-replaceable unit having a base and a projection. The projection can have a proximal portion and a distal portion, where the fastener is at least partially-threaded along the projection, and a plurality of seals are disposed radially along the projection. A channel can extend along a longitudinal axis of the fastener from the distal portion of the projection toward the proximal portion of the projection. One or more outlets can be disposed along the projection, the one or more outlets providing fluid communication between the channel and an external environment of the fastener. The fastener can be reversibly-coupled to a mating fastener of the structural manifold such that, when coupled, the line-replaceable unit is rigidly coupled to the structural manifold and fluid is able to flow therebetween.