Abstract: An electrical assembly comprises a plurality of modules (36), each module (36) including at least one switching element (38) and at least one energy storage device (40), the or each switching element (38) and the or each energy storage device (40) in each module (36) arranged to be combinable to selectively provide a voltage source, wherein each module (36) includes a respective sensor (46) that is configured to monitor at least one other of the plurality of modules (36), each sensor (46) configured to selectively detect an occurrence of an operational hazard in the or each corresponding monitored module (36).

Abstract: The rotor with a non-through shaft for a rotary electric machine comprises a cylindrical magnetic body clamped between two half-shafts, each comprising an attachment flange connected to the magnetic body, axial housings being uniformly provided in the magnetic body on at least one diameter of the magnetic body in order to house conductive bars. At least one attachment flange comprises insertion holes, each arranged facing a housing for inserting the conductive bars into the housings and the exterior diameter of the attachment flange is substantially equal to the exterior diameter of the magnetic body, the attachment flange comprising as many insertion holes as housings.

Abstract: There is provided a current control circuit (20) for connection between a first electrical network (42) and a converter, the current control circuit (20) comprising: first and second input terminals (24,26) for connection to the first electrical network (42); first and second output terminals (28,30) for respective connection to converter terminals (46,48) of the converter; first and second switching limbs, the first switching limb interconnecting the first input and output terminals (24,28), the second switching limb interconnecting the second input and output terminals (26,30), each switching limb including a respective switching element (32,34,36,38); a director limb (76) extending between the first and second output terminals (28,30), the director limb (76) including at least one current director element (84) and at least one first resistive element (86), the director limb (76) including an intermediate terminal (82); a second resistive element (88), a first end of the second resistive element (88) ope

Abstract: The conductor bar (17) for a squirrel-cage rotor comprises at least one end (17a) which is partially slit such that a section of the end forms two symmetrical branches (22, 23) relative to the slit (21). The centre of gravity (G3, G4) of each branch is arranged such that the branches flare towards the outside of the bar under the effect of centrifugal force when the rotor is rotated.

Abstract: Devices, systems, and methods for routing data to distributed devices in an aircraft are disclosed. A data routing system includes an aircraft and an equipment communicatively coupled to a control unit. The aircraft includes a control unit, and one or more distributed modules. The control unit is configured to communicate with each of the one or more distributed modules via an engine control bus. The control unit is configured to receive an Ethernet packet from the equipment via an Ethernet connection, translate protocols of the Ethernet packet to protocols for the engine control bus, identify an IP address in the Ethernet packet, and route data of the Ethernet packet to one of the one or more distributed modules over the engine control bus based on the IP address and the translated protocols.

Abstract: An additive manufacturing apparatus includes: a build table, at least a portion of which is transparent, the build table defining a build surface; a material applicator operable to deposit a radio-energy-curable resin on the build surface; a stage positioned facing the build surface of the build table and configured to hold a one or more cured layers of the resin; one or more actuators operable to change the relative positions of the build table and the stage; a radiant energy apparatus positioned adjacent to the build table opposite to the stage, and operable to generate and project radiant energy on the resin through the build table in a predetermined pattern; a drive mechanism operable to move the build table so as to expose a new portion thereof for each layer; and material remover operable to remove remnants from the build surface. A method for using the apparatus is provided.

Abstract: This electrical protection system for a DC-current medium-voltage electrical circuit, comprising a disconnection module, for generating a counter-voltage greater than the voltage of the source for a current flowing therethrough that is equal to at most a few percent of the nominal current of the device, a resistive limitation module connected between a first terminal and a second terminal and configured so as to reduce the intensity of the output current of the protection system in order to limit the current between a value and upon a low impedance fault downstream of the device, and a primary switching module coupled in parallel across the disconnection module and the resistive module. The primary switching module is configured so as to switch between a first state in which the primary switching module is conductive and a second state in which the primary switching module forms a short circuit.

Abstract: Disclosed herein are embodiments for providing altitude reporting. Some embodiments may include receiving a query from a first vehicle regarding altitude data of the first vehicle, providing the altitude data to the first vehicle, and receiving, by the computing device, a computed altitude from the first vehicle. Some embodiments include calculating an altitude uncertainty parameter for the first vehicle, determining a true altitude from the altitude data and the altitude uncertainty parameter, and determining whether the true altitude is within a predetermined threshold of a second altitude of a second vehicle. Some embodiments may be configured for, in response to determining that the true altitude is within the predetermined threshold, notifying at least one of the following: the first vehicle or the second vehicle.

Abstract: A method for making a container for retaining anesthetic agent. The method includes creating two or more parts each having a mating surface, where the container is formed when the mating surfaces of the two or more parts are coupled together, and where a first part of the two or more parts is formed of a material having pores defined within the mating surface thereof. The method further includes processing the mating surface of the first part via friction stir welding to reduce the pores defined therein. The method further includes coupling the two or more parts together such that the mating surfaces contact to create the container configured to retain the anesthetic agent therein.

Abstract: A method of analyzing a blended airfoil that includes generating a plurality of simulated blended airfoil designs each including one of a plurality of blend geometries, training surrogate models representing the plurality of simulated blended airfoil designs based on natural frequency, modal force, and Goodman scale factors, determining a likelihood of operational failure of each of the plurality of blended airfoil designs in response to one or more vibratory modes, determining which of the plurality of simulated blended airfoil designs violate at least one aeromechanical constraint and generating, a blend design space visualization including a blend design space, where the blend design space includes one or more restricted regions indicating blended airfoil designs where at least one aeromechanical constraint is violates and one or more permitted regions indicating blended airfoil designs where no aeromechanical constraints are violated.

Abstract: In the field of high voltage direct current (HVDC) power transmission networks, there is a need for improvements to allow a single power converter to control individual AC network voltages carried by multiple AC transmission conduits to multiple AC network elements, such as respective wind parks. A power transmission network (10; 100) comprises a power converter (12) which has first and second DC converter terminals (14, 16) that are for connection, in use, to a DC network. The power converter (12) also includes an AC converter terminal (22) which is electrically connected to a plurality of AC transmission conduits (241, 242, 24n), each of which is for connection, in use, to a respective AC network element (261, 262, 26n) that is configured to operate at a respective individual AC network voltage.

Abstract: There is provided a switching valve for a voltage source converter.

Abstract: A method for generating material test samples for conducting material tests of a legacy steam turbine rotor having an inter-blade region rotor surface, and an inlet region rotor surface adjoining the inter-blade region rotor surface. The method includes forming an annular ring of rotor material in the sample area and forming a material test sample from a portion of the annular ring. Also described is a legacy steam turbine rotor including an inter-blade region rotor surface, and an inlet region rotor surface adjoining the inter-blade region rotor surface. The steam turbine rotor having a groove formed therein, and wherein the groove is machined to enable removal of material from the steam turbine rotor to form samples configured to enable at least one of conducting material property tests and operating the improved legacy steam turbine rotor at an expanded thermal stress compared to the legacy steam turbine rotor.

Abstract: A storage tube assembly, with a cap having a top surface and a sealing member connected to the top surface, the sealing member has a generally cylindrical upper wall and a generally cylindrical lower wall, the sealing member also has a recessed portion between the upper wall and lower wall and a flange cut into the lower wall; a sealing ring, the sealing ring is sized to cooperate with and be received in the recessed portion of the sealing member of the cap; and a tube, the tube has a generally circular inner wall with a cut therein, the cut in the inner wall is positioned to receive the sealing ring when the sealing ring is positioned within the recessed portion of the cap and the cap is placed into an open end of the tube.

Abstract: According to various embodiments, an airfoil includes an outer wall defining an airfoil body surrounding at least one cavity and a removable insert including at least one mating feature for coupling the removable insert with the airfoil body between a first location within the at least one cavity and a second location within the at least one cavity. The removable insert is free of openings and separates a first air flow path from a second air flow path through the at least one cavity. Vanes and gas turbine engines including the airfoil are also disclosed.

Abstract: A method of determining a flight plan for an unmanned aerial vehicle comprises, with a computing device, receiving a set of parameters associated with a proposed flight operation related to the unmanned aerial vehicle, identifying one or more data sources that contain data associated with one or more of the parameters, retrieving data associated with one or more of the parameters from one or more of the identified data sources, determining a level of risk associated with the proposed flight operation based on the retrieved data, and determining the flight plan based on the level of risk.

Abstract: The rotor (4) for a squirrel-cage asynchronous rotating electrical machine comprises two compaction elements (6) clamping a cylindrical magnetic mass (7), short-circuit disks (8) inserted between the magnetic mass and the compaction elements, and conductive bars (9) housed in housings (10) of the magnetic mass and evenly distributed over at least one diameter of the magnetic mass, so that the short-circuit disks and the conductive bars form a squirrel-cage, at least one of the compaction elements and the short-circuit disks comprising insertion holes (Sa, 12) each disposed facing a housing. Retention means are inserted into each insertion hole to retain the conductive bars in the housings.

Abstract: In the field of high voltage direct current (HVDC) power transmission networks there is a need for an improved power converter. A power converter, for use in a HVDC power transmission network, comprises first and second DC terminals, for connection in use to a DC network and between which extends at least one converter limb. The or each converter limb includes first and second limb portions which are separated by an AC terminal, for connection in use to an AC network. Each limb portion includes a switching valve, and the power converter including a controller programmed to control switching of the switching valves to control the flow of a converter current (Imax) through the power converter and thereby in-use transfer power between the power converter and the AC network. The power transferred between the power converter and the AC network has an active component and a reactive component.

Abstract: A rotor disk for a gas turbine engine includes a disk body having a central bore extending therethrough. The disk body includes a bore body that extends around the central bore, a web that extends radially outward from the bore body having decreased thickness relative to the bore body and a peripheral rim that is located at an outer end of the web. The peripheral rim includes blade mounting structures for engaging complimentary mounting structures of rotor blades. The bore body has a bore cavity that extends continuously through the bore body and about an entire periphery of the central bore. The bore cavity has a central axis that forms a circle about the central bore.

Abstract: A method of providing an indication identifying a flight as including or not including a flight path deviation, the method includes receiving flight data associated with a flight, the flight data comprising a plurality of coordinates indicating a location of an aircraft at a plurality of times during the flight. The method also includes classifying a plurality of time intervals of the flight by applying a convolutional neural network algorithm to subsets of the plurality coordinates to determine that the time interval includes or does not include at least one flight path deviation. The method also includes identifying the flight as including at least one flight path deviation if at least one of the time intervals is classified as including the at least one flight path deviation and providing an indication identifying the flight as including at least one flight path deviation to a second computing system in response to identifying the flight as including at least one flight path deviation.

Abstract: An apparatus may receive first data, in a first data format, from one or more unmanned aircraft system service suppliers comprising first positions of one or more unmanned aircraft systems, receive second data, in a second data format, from one or more communications systems comprising second positions of one or more manned aircraft, transmit third data, in a third data format, comprising the first positions of the one or more unmanned aircraft systems and the second positions of the one or more manned aircraft, receive a first control signal comprising a control command associated with one or more of the unmanned aircraft systems or one or more of the manned aircraft, and transmit a second control signal comprising the control command to one or more of the unmanned aircraft system service suppliers or to one or more of the communications systems.

Abstract: A method for manufacturing a dual-structured aircraft engine starting and generating apparatus is provided. The method includes printing a housing using a three-dimensional printing process including a main machine portion and an exciter portion for receiving at least part of a generator system. Printing the housing includes printing a cooling jacket portion comprising one or more cooling passages that is a monolithic part of a sidewall of the housing.

Abstract: A method of operating an aircraft interface device may comprise receiving a request for a data dictionary from an electronic flight bag application and transmitting the data dictionary to the electronic flight bag application. The data dictionary may comprise a mapping between a plurality of parameters associated with an aircraft and a plurality of parameter identifiers. Values of the parameters may be retrieved by the aircraft interface device. The method may also include receiving a request for values of one or more of the parameters from the electronic flight bag, retrieving values of the parameters, and transmitting the values of the parameters to the electronic flight bag application.

Abstract: A mixer for recirculating ash from solid fuel combustion with hydrated lime and water and to feed the mixture into a desulfurization reactor. The mixer includes a housing having a front wall, two outer vertical sidewalls, a rear wall, a top, and a bottom, the top includes a feed chute configured for the entry and addition of product to the mixer, and the front wall includes an opening for the mixture of product to exit. The mixer also includes a rotatable vertical shaft having an impeller, the impeller having a plurality of blades disposed on the vertical shaft in the same horizontal plane and distributed equidistantly about the circumference of the vertical shaft. The mixer also includes a vertical wall disposed within the housing forming a mixing region and a feeding region that is operably connected to the opening of the front wall.

Abstract: A method of performing deconfliction comprises receiving a request to accept a first operational intent associated with a first unmanned aircraft system, determining whether a conflict exists between the first operational intent and one or more scheduled operational intents, and if a conflict exists between the first operational intent and a second operational intent associated with a second unmanned aircraft system, transmitting data associated with the conflict to a first operator of the first unmanned aircraft system and a second operator of the second unmanned aircraft system, and transmitting information to the first and second operator allowing them to negotiate a resolution of the conflict. If a conflict does not exist, the first operational intent may be accepted. Bids may also be received for a right to utilize a volume of airspace at a particular time and the right may be granted to a highest bidder.

Abstract: A method of performing fault isolation for an aircraft comprises identifying a fault that occurs during a flight of the aircraft; identifying a first set of parameters associated with the aircraft based on the identification of the fault; automatically determining values of the first set of parameters to obtain a first set of measured values; determining whether the first set of measured values are within acceptable ranges; and identifying a source of the fault based on the determination of whether the first set of measured values are within the acceptable ranges.

Abstract: A method for producing a component from two or more sub-components includes the steps of: producing each of the sub-components using an additive manufacturing process in which a resin, which is radiant-energy-curable, is partially cured using a selective application of radiant energy, wherein each sub-component includes a joint surface in which the resin is partially cured which is cured to a lesser degree than the remainder of the respective sub-component, so as to leave the joint surfaces in a condition suitable for bonding; assembling the sub-components with their respective joint surfaces in mutual contact; and performing a secondary cure of the partially-cured resin at the joint surfaces using an application of radiant energy, so as to further cure the partially-cured resin and bond the sub-components to each other, thereby forming the component.

Abstract: A generator assembly includes a stator assembly coupled to an engine stator component of a propulsion engine, the stator assembly including: a stator support structure fixedly attached to the engine stator component; a stator disposed on a supporting surface of the stator support; a manifold coupled to the stator support, the manifold defining a connection volume and including at least one coolant opening at a connection end of the manifold; and an electrical connector extending between the stator and a connection device disposed on the connection end. The generator assembly also includes a rotor assembly comprising a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure, wherein the rotor rotates in conjunction with the shaft to generate a power signal that travels through the electrical connector to the connection device.

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: One embodiment includes a multistage infrared suppression exhaust system for an aircraft, including: a stage one including a first exhaust conduit to receive a first exhaust air flow at a first temperature-pressure product T1P1, a second exhaust conduit to receive a second exhaust air flow at a second temperature-pressure product T2P2, and a flow integrator mechanically configured to mix the first exhaust air flow with the second exhaust air flow in an integration chamber while preventing back pressure into the second exhaust conduit; and a stage two including a stage two cooling airflow to cool the mixed first and second exhaust air flows.

Abstract: A load adaptive linear electrical generator system is provided for generating DC electrical power. The electrical generation system includes one or more power generation modules which will be selectively turned on or off and additively contribute power depending on the DC power demand. Each power generating module includes a pair of linear electrical generators connected to respective ones of a pair of internal combustion piston based power assemblies. The piston in the internal combustion assembly is connected to a magnet in the linear electrical generator. The piston/magnet assembly oscillates in a simple harmonic motion at a frequency dependent on a power load of the electrical generator. A stroke limiter constrains the piston/magnet assembly motion to preset limits.

Abstract: A load adaptive linear electrical generator system is provided for generating DC electrical power. The electrical generation system includes one or more power generation modules which will be selectively turned on or off and additively contribute power depending on the DC power demand. Each power generating module includes a pair of linear electrical generators connected to respective ones of a pair of internal combustion piston based power assemblies. The piston in the internal combustion assembly is connected to a magnet in the linear electrical generator. The piston/magnet assembly oscillates in a simple harmonic motion at a frequency dependent on a power load of the electrical generator. A stroke limiter constrains the piston/magnet assembly motion to preset limits.

Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A turbomachine engine can include an unducted fan assembly, an unducted vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The unducted fan assembly can include a plurality of fan blades. The unducted vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the unducted fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: External External loading test apparatus comprising: a structure with at least three pillars supporting a platform, the platform being configured to receive a podded electric propulsion motor in a hanging position while allowing operation of said pod, at least a test subsystem, for applying a force on the pod to simulate full scale external loading.

Abstract: An apparatus for breaking apart a substance is provided. The apparatus includes a body configured to be selectively secured via a fastener between two surfaces of a container and to break apart the substance upon impact. At least a portion of the body is operative to drop towards a bottom surface of the container upon removal of the fastener so as to facilitate removal of the substance from the container.

Abstract: An additive manufacturing machine includes: a resin support which has at least a portion which is transparent, wherein the resin support defines a build surface; a material depositor operable to deposit a resin which is radiant-energy-curable onto the build surface; at least two build stations, each build station including: a stage positioned adjacent the build zone and configured to hold a stacked arrangement of one or more cured layers of the resin; one or more actuators operable to manipulate a relative position of the stage and the build surface; and at least one radiant energy apparatus positioned opposite to the stage, and operable to generate and project radiant energy in a predetermined pattern.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A light detection and ranging (LiDAR) system includes light sources configured to generate separate beams of light, a lens array configured to receive the separate beams of light from the light sources and to collimate the separate beams of light into collimated outgoing light that is directed toward an examined area of interest, a light sensitive detector configured to sense reflection of at least part of the collimated outgoing light, and one or more processors configured to determine a distance to one or more objects off which the at least part of the collimated outgoing light was reflected toward the light sensitive detector. The one or more processors are configured to determine the distance based on the reflection of the at least part of the collimated outgoing light.

Abstract: The present disclosure generally relates to additive manufacturing systems and methods involving a mechanism for feeding in a desired amount of fresh recoater blade. This can be accomplished by, for example, spooling the fresh blade material from a spool. This helps prevent work stoppage when a portion of a recoater blade becomes damaged. As such, the present disclosure also relates to a system and method for detecting whether a recoater blade is damaged, and if there is damage, then causing a fresh blade portion to be fed in.

Abstract: This mechanical system for rotating electric machine comprises at least one rotor and at least one transmission shaft for mechanical device. The rotor has a non-through shaft and comprises a cylindrical magnetic block enclosed between a first and a second raised compaction elements forming a rotor shaft, with one end of the transmission shaft being connected directly to the first compaction element.

Abstract: A method of controlling of a polyphase power converter driven by an algorithm of the pulse width modulation type, in which a control parameter comprising a drive setpoint value or a pulse duration associated with a value of drive setpoint of at least one phase, situated in a non-linearity zone of a chart, is modified by modifying the value of said parameter so that it is in a linearity zone of the chart. The control parameter of each of the phases is modified in the same manner.

Abstract: A system and method of controlling corrosion of a heat exchanger, having a hot gas inlet and outlet and a cold side inlet and outlet. The method includes determining a temperature of the heat exchanger at a first selected location, controlling a temperature of a corrosion sensing device to a first selected temperature based on the temperature of the surface of the heat exchanger and determining a corrosion rate associated with the heat exchanger surface at the first selected location for the first selected temperature. The method also includes comparing the corrosion rate to an expected corrosion rate, determining a cold side fluid inlet temperature target for the heat exchanger based at least in part on the comparing, the determined corrosion; and controlling a cold side fluid inlet temperature based at least in part on the determined inlet temperature target, determined corrosion rate, and expected corrosion rate.

Abstract: A method for fabricating a component of with an additive manufacturing system include entraining a first portion of first material particles in an airflow generated by a vacuum source and engaging the first portion of the first material particles against an air permeable screen. The first portion of the first material particles is deposited onto a build platform. The method also includes entraining a second portion of second material particles in the airflow and engaging the second portion of the second material particles against the air permeable screen. The second portion of the second material particles is deposited onto the build platform. An energy source transfers heat to at least a portion of at least one of the first portion of the first material particles or the second portion of the second material particles to facilitate consolidating material particles to fabricate the component.

Abstract: A disconnector to reduce considerably high voltage and high frequency current generated during the service no-load opening and closing, the disconnector comprising a first main contact a second main contact, a sliding contact and an arcing horn having a length, the disconnector having a connected state, an intermediate state and a disconnected state, wherein in the connected state a first electrical contact is established between the first main contact and the second main contact, in the intermediate state the first electrical contact is interrupted while a second electrical contact exists between the sliding contact and a contact position on the length of the arcing horn, and in the disconnected state the first electrical contact and the second electrical contact are interrupted, wherein at least a part of the length of the arcing horn comprises an electrical filter configured to provide a resistance and an inductance to an electrical current.

Abstract: A device comprises: a high temperature semiconductor device comprising a first surface, wherein the high temperature semiconductor device comprises an active area and a termination area disposed adjacent to the active area; an inorganic dielectric insulating layer disposed on the first surface, wherein the inorganic dielectric insulating layer fills a volume extending over an entirety of the termination area and comprises a thickness greater than or equal to 25 ?m and less than or equal to 500 ?m; and an electrical connector connecting the active area of the high temperature semiconductor device to an additional component of the device.

Abstract: An infant warming system includes a bassinet having a platform configured to support an infant, at least one wireless physiological sensor configured to measure a physiological parameter from the infant and transmit physiological parameter data, and at least two radio frequency identification (RFID) readers. The RFID readers are configured to communicate with the at least one wireless physiological sensor to facilitate pairing therewith so as to enable receipt of the physiological parameter data from the wireless physiological sensors at the infant warmer system. The RFID readers each have a range distance that is less than a length of the platform and are positioned such that the wireless physiological sensor is in the range distance of at least one of the at least two RFID readers from any location on the platform.

Abstract: A method of providing an abstraction layer between an application layer and one or more existing hardware components of a computing device includes receiving a request for a resource from the application layer, determining a component type for performing a task according to the request for the resource, determining whether the one or more existing hardware components of the computing device correspond to the component type for performing the task based on a predetermined function of the one or more existing hardware components, converting the task into a translated task readable by the one or more existing hardware components, providing the translated task to the one or more existing hardware components, receiving an output from the one or more existing hardware components as a result of providing the translated task, and providing the output to the application layer as an emulated output that mimics an expected output of the component type.