Abstract: A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

Abstract: A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

Abstract: Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

Abstract: A method for correcting a synthesized speech set for hearing aid according to an aspect of the present invention includes the steps of outputting first synthesized speech for testing on the basis of first synthesized speech data for testing correlated with a first phoneme label in a synthesized speech set for testing, accepting a first answer selected by a user, outputting second synthesized speech for testing on the basis of second synthesized speech data for testing correlated with a second phoneme label in the synthesized speech set for testing, accepting a second answer selected by the user, and correlating first synthesized speech data for hearing aid with the second phoneme label instead of second synthesized speech data for hearing aid in a synthesized speech set for hearing aid, in a case in which the first answer matches the second phoneme label and also the second answer does not match the second phoneme label.

Abstract: A process for the production of a layer structure of a nitride semiconductor component on a silicon surface, comprising: provision of a substrate having a silicon surface; deposition of an aluminium-containing nitride nucleation layer on the silicon surface of the substrate; optional: deposition of an aluminium-containing nitride buffer layer on the nitride nucleation layer; deposition of a masking layer on the nitride nucleation layer or, if present, on the first nitride buffer layer; deposition of a gallium-containing first nitride semiconductor layer on the masking layer, wherein the masking layer is deposited in such a way that, in the deposition step of the first nitride semiconductor layer, initially separate crystallites grow that coalesce above a coalescence layer thickness and occupy an average surface area of at least 0.16 ?m2 in a layer plane of the coalesced nitride semiconductor layer that is perpendicular to the growth direction.

Abstract: A process for the production of a layer structure of a nitride semiconductor component on a silicon surface, comprising: provision of a substrate having a silicon surface; deposition of an aluminium-containing nitride nucleation layer on the silicon surface of the substrate; optional: deposition of an aluminium-containing nitride buffer layer on the nitride nucleation layer; deposition of a masking layer on the nitride nucleation layer or, if present, on the first nitride buffer layer; deposition of a gallium-containing first nitride semiconductor layer on the masking layer, wherein the masking layer is deposited in such a way that, in the deposition step of the first nitride semiconductor layer, initially separate crystallites grow that coalesce above a coalescence layer thickness and occupy an average surface area of at least 0.16 ?m2 in a layer plane of the coalesced nitride semiconductor layer that is perpendicular to the growth direction.

Abstract: The disclosure provides a method for correcting a 1 pulse per second (1PPS) signal and a timing receiver. In the embodiments of the disclosure, the proposed method allows the timing receiver to provide a corrected 1PPS signal with better quality to back-end slave devices, thereby ensuring that the synchronization effect of the slave devices is not overly affected by jitter in a single 1PPS signal.

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

Abstract: A first spacecraft comprises a drive mechanism. A second spacecraft comprises a valve for filling/draining the second spacecraft. The coupling assembly comprises a first connector comprising an actuating member configured to engage and open the valve and a coupling member configured to couple to the drive mechanism. A second connector comprises a stop portion and a bore for transferring fluid. Operation of the drive mechanism rotates the coupling member and the second connector together to screw the second connector onto the valve until the stop portion engages the valve, the actuating member being prevented from moving relative to the second connector to open the valve whilst the lock is in the locked state. Once the stop portion engages the valve, operation of the drive mechanism to exert a torque on the coupling member greater than a predetermined torque level moves the lock to an unlocked state wherein the actuating member is moveable relative to the second connector to engage and open the valve.

Abstract: A lighting device is provided. The lighting device includes: a lighting unit in which a plurality of light sources are mounted; a lighting cover installed to be spaced apart from the lighting unit; and a reflective sheet arranged on a light source mounting surface of the lighting unit and reflecting reflected light reflected from the lighting cover back toward the lighting cover, wherein wavelength conversion layer for converting a wavelength of the reflected light reflected from the lighting cover is laminated on the reflective sheet.

Abstract: A launch system and method for orbital or suborbital air-launch of a payload involving releasably coupling a launch vehicle with a towed aircraft via an articulatable carriage to form an air-launch assembly, towing the air-launch assembly via a tow aircraft and interconnected tow cable to a first altitude, releasing the air-launch assembly from tow at or above the first altitude, activating the towed aircraft propulsion system and initiating a pull-up and climb maneuver of the towed aircraft to a second altitude, articulating the articulatable carriage to shift the air-launch assembly from a stowed position to a deployed position with the launch vehicle spaced from the towed aircraft, releasing the launch vehicle from the articulatable carriage and thus from the towed aircraft, and activating the launch vehicle propulsion system for further altitude gain or to meet specific mission requirements.

Abstract: A non-immersive virtual reality (NIVR) method includes receiving sets of images of a first user and a second user, each image from the sets of images being an image of the associated user taken at a different angle from a set of angles. Video of the first user and the second user is received and processed. A first location and a first field of view are determined for a first virtual representation of the first user, and a second location and a second field of view are determined for a second virtual representation of the second user. Frames are generated for video planes of each of the first virtual representation of the first user and the second virtual representation of the second user based on the processed video, the sets of images, the first and second locations, and the first and second fields of view.

Abstract: A system, is disclosed having a polymer-based additive manufacturing subsystem, a metallic-based additive manufacturing subsystem, an exchanger to place at least one of the polymer-based additive manufacturing subsystem and the metallic-based additive manufacturing subsystem into a position to provide a manufacturing process, a build area where a part is created with the polymer-based additive manufacturing subsystem and the metallic-based additive manufacturing subsystem, and an environmental control unit to collect debris produced during operation of the polymer-based additive manufacturing subsystem and the metallic-based additive manufacturing subsystem. Another system and method are also disclosed.

Abstract: A process for the production of a layer structure of a nitride semiconductor component on a silicon surface, comprising: provision of a substrate having a silicon surface; deposition of an aluminium-containing nitride nucleation layer on the silicon surface of the substrate; optional: deposition of an aluminium-containing nitride buffer layer on the nitride nucleation layer; deposition of a masking layer on the nitride nucleation layer or, if present, on the first nitride buffer layer; deposition of a gallium-containing first nitride semiconductor layer on the masking layer, wherein the masking layer is deposited in such a way that, in the deposition step of the first nitride semiconductor layer, initially separate crystallites grow that coalesce above a coalescence layer thickness and occupy an average surface area of at least 0.16 ?m2 in a layer plane of the coalesced nitride semiconductor layer that is perpendicular to the growth direction.

Abstract: A balloon system including a balloon, and optionally including a payload and/or a safety module. A balloon, preferably including a balloon envelope and one or more passive vents, and optionally including one or more active valves. A method of balloon system operation, preferably including maintaining a zero-pressure balloon condition and sealing balloon vents, and optionally including ascending, descending, and/or otherwise operating the balloon system in flight.

Abstract: Systems, methods, and non-transitory media are provided for cross-coupling modeling and compensation. An example method can include determining one or more cross-coupling coefficients representing electrical cross-coupling within a component of a phased array antenna, wherein the component of the phased array antenna includes one or more signal paths between one or more beamformers of the phased array antenna and a set of antenna elements of the phased array antenna; based on the one or more cross-coupling coefficients, modifying one or more beamforming weights calculated for one or more signals routed via the one or more signal paths, wherein the modified one or more beamforming weights compensate for the electrical cross-coupling effect within the component of the phased array antenna; and applying, by the one or more beamformers, the modified one or more beamforming weights to the one or more signals routed via the one or more signal paths.

Abstract: This invention relates generally to ionogram image processing, autoscaling and inversion systems and methods for ionospheric monitoring, modeling, and estimation of the same. One advantage of the present invention is to provide a system, e.g., a lightweight, low-power, and fully-autonomous ionospheric monitoring system that is able to provide fully processed and highly accurate ionosphere characterization in near real-time over a low data-rate satellite link.