Abstract: A circuit has at least one amplifier and a signal routing device such as one or more switches, and an array of antenna elements from which some subset must be enabled and processed at a time. The antenna elements can be grouped in accordance with an organization scheme (e.g., rows, columns) to enable more flexibility in selecting and routing the signals. The system is used to create one or more beams, which can be pointed (steered) to a wide range of directions by means of selecting one or more feed antennas in a switched-feed antenna without including full receive and transmit circuitry (DSP, frequency conversion) for each feed in the array. In this case, minimizing the number of DSP chains is desirable to reduce the cost, power, and complexity of the antenna. The resulting beam(s) can be combined and manipulated to support multiple users, track several targets, increase operational range, increase radar resolution, or data-rate in communications.

Abstract: A semiconductor layer stack, a component made therefrom, a component module, and a production method is provided. The semiconductor layer stack has at least two layers (A, B), which, as individual layers, each have an energy position of the Fermi level in the semiconductor band gap, E F - E V < E G 2 applying to the layer (A) and E L - E F < E G 2 applying to the layer (B), with EF the energy position of the Fermi level, EV the energy position of the valence band, EL the energy position of a conduction band and EL?EV the energy difference of the semiconductor band gap EG, the thickness of the layers (A, B) being selected in such a way that a continuous space charge zone region over the layers (A, B) results.

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: This invention relates to a method for optimising usage 5 of electricity from the grid and energy storage comprising: forecasting a predetermined number of hours of load at a predetermined interval to determine a forecasted load profile; subtracting a peak load from the forecasted load profile by a maximum amount of electricity that can be charged into or discharged from the energy storage to determine a subtracted peak; smoothening peaks 10 within 30 minutes period that are more than the subtracted peak to obtain a final forecast result; and determining optimised battery setpoint actions based on the final forecast result and energy storage operating constraints.

Abstract: An air to air refueling system that monitors and adapts the movement at an end of an air to air refueling hose of a tanker aircraft to counteract undesirable movements at the end of the hose though generating aerodynamic loads in the end of the hose. The system includes grid fins at the end of the hose that are automatically rotated to counteract the undesirable movements.

Abstract: To provide a connection adapter and a horn antenna measurement device capable of measuring the performance of a system of a horn antenna on the ground without removing the horn antenna mounted on a spacecraft even immediately before the launch, while suppressing radio wave leakage to an external space. A connection adapter (200) includes a first waveguide (201) that is provided inside the connection adapter and connected to a waveguide portion (260) connected to a horn antenna (100), in which the connection adaptor is detachably fitted into the horn antenna, is connected to a measurement instrument (300) via a second waveguide (250) coupled to the first waveguide, and guides radio waves radiated from the horn antenna to the measurement instrument in a closed system.

Abstract: A modular satellite apparatus for testing materials in a space setting is provided. The apparatus includes a lower member and an upper member, as well as rear support members, medial support members, front support members, and side members that each extend between the lower member and the upper member. They apparatus also includes attachment members connected to an external surface of the lower member and configured to connect to an external platform. The apparatus further includes a plurality of mounting members on an internal surface of the lower member or the side members, and a plurality of heatsinks. The lower member includes a plurality of heatsink receiving holes formed therein to receive portions of the heatsinks to connect the heatsinks to the lower member.

Abstract: Methods, non-transitory computer readable media, and verifier and/or prover devices or query verification apparatuses are disclosed that generate a first commitment from received data and send the received data to a prover device for insertion into a table of a database. A query result and an overall proof are received from the prover device in response to a received query forwarded to the prover device and associated with the database table. The overall proof is generated from one or more partial proofs comprising one or more commitments generated from one or more intermediate values. The query result and an indication the query result was verified are returned in response to the received query after verifying the query result based on a second commitment to the query result generated using the first commitment and the overall proof.

Abstract: For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method further iteratively calculates an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. In response to determining the inner polytope boundary will be breached, the method maneuvers the given spacecraft to within the inner polytope boundary based on a switching condition, a guidance law, and model predictive control to minimize fuel consumption.

Abstract: An apparatus includes an integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring. In a spacecraft application, a spacecraft appendage may be coupled with a deployment mechanism, the deployment mechanism including at least one integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring.

Abstract: A miniaturized coupling for jewelry includes a male coupling and a female coupling, each of which is millimeter-sized or sub-millimeter-sized and each of which is attached to or suited to be attached to a respective jewelry component. The male coupling has a locking member configured to be inserted into the female coupling through an opening into an interior of the female coupling. A resiliently-biased, snap connector located in the interior of the female coupling, so constructed that when the locking member is inserted into the female coupling it initially moves and then is retained by the snap connector. An actuating pin in the female coupling is configured to move the snap connector to release the locking member and thereby disengage the male and female couplings from each other. The actuating pin has an outer surface accessible at an outer surface of the female coupling.

Abstract: Systems and methods herein provide for Multi-Input/Multi-Output (MIMO) processing. In one embodiment, a MIMO system comprises a receiver operable to receive a plurality of spatially multiplexed data streams. The system also comprises a processor operable to embed a maximum likelihood (ML) detection algorithm onto a quantum annealer, and to decode the spatially multiplexed data streams via the embedded ML to detect data bits of a plurality of users.

Abstract: A method of preparing hexagonal boron nitride (h-BN) fibers includes mixing polyvinylpyrrolidone (PVP) and boron oxide (B2O3) to form a polymer precursor or mixing PVP and ammonia borane (BH3NH3) to form the polymer precursor. The method includes forcespinning the polymer precursor to form fibers of the polymer precursor, curing the fibers to form polymer fibers, and pyrolyzing the polymer fibers to form the h-BN fibers.

Abstract: In some embodiments, an apparatus includes a first layer having a first plurality of electrically conductive traces comprising a first portion of a plurality of hierarchical networks; a second layer having a second plurality of electrically conductive traces comprising a second portion of the plurality of hierarchical networks; and a plurality of vias electrically connecting the first plurality of electrically conductive traces of the first layer to the respective second plurality of electrically conductive traces of the second layer to define the plurality of hierarchical networks. The first plurality of electrically conductive traces is orientated in a first direction and the second plurality of electrically conductive traces is orientated in a second direction different from the first direction.

Abstract: A vapor phase epitaxy method of growing a III-V layer with a doping that changes from a first conductivity type to a second conductivity type on a surface of a substrate or a preceding layer in a reaction chamber from the vapor phase from an epitaxial gas flow comprising a carrier gas, at least one first precursor for an element from main group III, and at least one second precursor for an element from main group V, wherein when a first growth height is reached, a first initial doping level of the first conductivity type is set by means of a ratio of a first mass flow of the first precursor to a second mass flow of the second precursor in the epitaxial gas flow, the first initial doping level is then reduced to a second initial doping level of the first or low second conductivity type.

Abstract: In situ alloying of elemental Cu, Cr, and Nb powder using laser melting to form a Cu—Cr2Nb alloy. The elemental powders are initially mixed to form a homogeneous mixture, which mixture is then subjected to laser radiation to melt the mixture. In the melt, the Cr and Nb react to form Cr2Nb, which when cooled form precipitates that are dispersed in a nearly pure Cu matrix to thus dispersion strengthen the material. The methods can be used to additively manufacture a 3D component of Cu—Cr2Nb alloy using a selective laser melting machine.

Abstract: A method for producing a satellite to facilitate the inclusion of one or more reflector antennas on a surface of the satellite is disclosed. A reusable generic configuration is determined in advance separately from the satellite mission. The generic configuration generally features the following parameters for each reflector: diameter, focal distance, offset distance of the reflector in the deployed position, position of the deployment device, position of the radiofrequency source. The generic configuration is determined such that an antenna points by default towards the centre of the earth when its reflector is in a deployed position. A specific configuration step then consists of defining a limited number of specific parameters depending on the satellite mission. The specific configuration is rendered possible in particular by controlling the deployment device, i.e., by changing the direction in which the antenna points, once the reflector has been deployed.

Abstract: A two-part coupling for use in joining sections of pipe without additional fasteners is disclosed. The two-part coupling includes integral coupling features molded by additive manufacturing technology. The two-part coupling increases reliability, reduces weight, and provides ease of manufacture. The coupling distributes a fluid load so that the coupling can withstand pressures and leak rates in accordance with stringent standards. The two-part coupling can be coupled and de-coupled using a locking and release mechanism built into the integral parts. Assembly is made easier because the geometry of the coupling is amenable to additive manufacturing. Because the two-part coupling requires a lesser degree of precision, machined parts are not required.

Abstract: An attitude control system for a satellite is presented that can determine on time values for attitude control thrusters without use of attitude rate sensors, such as those based on gyros. The attitude control systems uses the attitude values from a star tracker to determine both attitude adjustment values and attitude adjustment rate values directly from the star tracker values, where the processing is performed using quaternions. From the attitude adjustment values and attitude adjustment rate values, a set of thruster on time values are determined.

Abstract: A pulsar-based timing and lateration system includes a detector system. In according with certain embodiments, the detector system includes a plurality of detectors, each one configured for detecting X-ray photons and generating output signals according to the X-ray photons detected, and an electronics unit for receiving and analyzing the output signals from the detectors. The electronics unit includes a processor for analyzing the output signals received from the detectors. A first detector is aimed toward a first pulsar such that the X-ray photons detected at the first detector includes pulsar signals from the first pulsar. The processor includes a memory for storing a library of data related to electromagnetic emissions of known pulsars. The processor isolates the pulsar signals from the first pulsar, and determines position and velocity of the system by comparing the isolated pulsar signals to the library of data.