Abstract: A power transistor includes an ambient temperature input, a local temperature sensor, an array of transistor cells, and a thermal feedback circuit. The ambient temperature input is configured to receive an ambient temperature signal that is representative of an ambient temperature of the power transistor. The array of transistor cells has a control input. The local temperature sensor is configured to provide a local temperature signal that is representative of a temperature of the array of transistor cells. The thermal feedback circuit is coupled to the ambient temperature input, the local temperature sensor, and the control input. The thermal feedback circuit is configured to modulate a control signal provided at the control input based on a difference between the ambient temperature signal and the local temperature signal.

Abstract: An aircraft wing structure includes first and second unitary shell structures formed from a fiber-reinforced composite material. Each shell structure includes a partial front spar, a partial rear spar and a wing skin. The partial front spars of each shell structure and the partial rear spars of each shell structure are arranged to overlap to form front and rear spars respectively. A wing box structure is lightweight, strong and durable, with a lower overall part count than has been conventionally achievable. Aircraft systems equipment may be attached to the shell structures prior to, or after, assembly into a wing box.

Abstract: Disclosed are systems, methods, and media capable of generating and implementing emergency flows. The emergency flow is highly customizable and can connect with various stakeholders (user, emergency contacts, corporate representatives, emergency service provider personnel, etc.). The systems, methods, and media can be triggered in various ways including user input (e.g. voice command) or by sensors (e.g. by using sound detection capabilities).

Abstract: A disclosed monitoring system includes infrared light sources that illuminate a subject in a sequenced manner and a camera that captures images of the subject during periods in which the subject is illuminated by one of the light sources. The system includes a processor that analyzes captured images to determine a brightness measure of the images, and a controller controls output power of the infrared light sources in response to the brightness measure. In response to the processor detecting a brightness measure below a predetermined brightness threshold, the controller is configured to switch off or reduce an output illumination intensity of one of the infrared light sources. A disclosed method further determines whether an emission source is occluded by modulating an intensity of an electromagnetic emission source, detecting whether the modulation pattern is present in captured images, and determining that the emission source is occluded based on the detected modulation.

Abstract: An HHO gas second fuel is produced in a pressure-resistant container and distributed at a low volumetric rate at multiple locations about the internal combustion engine.

Abstract: Described herein is a method (1000) of detecting mobile device (400) use of a driver (102) of a vehicle (104). The method (1000) comprises the step (1001) of receiving a sequence of images of at least the driver's head captured from a camera (106, 420). At step (1002), the sequence of images are processed to determine visual attention of the driver (102) based on detected head and/or eye movements of the driver (102) over a period of time. At step (1003), mobile device use events are detected within the period of time in which a user interacts with the mobile device (400) that is located within the vehicle (104). At step (1004), a temporal correlation of the visual attention of the driver (102) with the mobile device use events is determined over the period of time. At step (1005), a determination is made that the driver (102) is using the mobile device (400) if the determined temporal correlation is greater than a threshold correlation coefficient.

Abstract: A method is provided for determining a unique identifier of a device, the devise including a quantum tunnelling barrier unique to the device. The method comprises applying a potential difference across the quantrum tunnelling barrier, the potential difference sufficient to enable tunnelling barrier. The method further comprises measuring an electrical signal, the electrical signal representative of a tunnelling current through the quantrum tunnelling barrier. The method further comprises determining, from the measured electrical signal, a unique identifier for the device. Related apparatuses, systems, computer-readable media and methods are also provided herein.

Abstract: An aircraft structure including a first surface and a second surface. The first surface and the second surface are bonded together via a plurality of discrete adhesive sections arranged in a herringbone pattern or a support between the first surface and the second surface, wherein the support includes spaced apart ribs with discrete adhesive sections located between the spaced apart ribs.

Abstract: A wing-box structure for an aircraft is disclosed having an upper cover, a lower cover, longitudinal forward and rearward spars, and a plurality of transverse ribs. One of the transverse ribs is retained by a pair of opposed captive features disposed on an interior side of either the forward and rearward spars or the upper and lower covers. The rib is bonded rib to the forward and rearward spars and/or the upper and lower covers at a location where the rib is retained.

Abstract: An aircraft wing is disclosed including a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. An inductive coupler is arranged to inductively transmit data and/or power between the main wing element and the movable wing tip device. The inductive coupler removes the need for wires and cables to pass across a joint between the main wing element and a movable wing tip device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to transmit data and/or power between the main wing element and the movable wing tip device.

Abstract: An aircraft is disclosed having a device and an aircraft wing. The aircraft wing includes a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device includes an accumulator configured to store energy and the movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. The accumulator is configured to transmit power to the device. The accumulator enables energy to trickle between the main wing element and the movable wing tip device whilst still providing a suitable power source to the device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to store energy in the movable wing tip device.

Abstract: The present disclosure generally relates to a surface grating in a photodetector device. In an example, a semiconductor device structure includes a photodetector device. The photodetector device includes one or more photodiodes disposed in or over a semiconductor substrate, and includes a surface grating disposed at a respective surface of each photodiode of the one or more photodiodes. The surface grating has one or more periodicities. Each periodicity of the one or more periodicities has a period that is along a direction parallel to a first lateral direction across the semiconductor substrate and that is equal to or less than half of a dimension of at least one photodiode of the one or more photodiodes along a direction parallel to the first lateral direction. The one or more periodicities includes multiple different pitches.

Abstract: A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor. An aircraft structure, for example a wing, includes a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing).

Abstract: A small to mid-scale liquefied natural gas production system and method is provided. The disclosed liquefied natural gas production system employs at least one heat exchanger, three turbine/expanders and at least three refrigerant compression stages. The expansion ratio of one turbine/expander is appreciably lower than the expansion ratio of the other turbine/expanders such that the temperature of the exhaust stream from the turbine/expander with the lower expansion ratio is above the critical point temperature of the compressed natural gas containing feed stream but colder than about ?15° C. The present system and method may be configured using either a single nitrogen-based expansion refrigerant circuit or two separate refrigerant circuits wherein the turbine/expander with the lowest expansion ratio is contained within a separate refrigeration circuit from the other two turbine/expanders with the higher expansion ratios.

Abstract: A wing assembly for an aircraft is disclosed having a wing and a wing tip device at the tip of the wing, wherein the wing tip device is moveable between a flight configuration and a ground configuration. The wing has a spar extension which extends spanwise away from a distal end of the wing, the spar extension having a first end portion fixed in the wing and a second end portion which, in the flight configuration, is disposed in the wing tip device such that, in the flight configuration, the spar extension transmits flight loads between the wing tip device and flight-load bearing structure in the wing. The wing assembly may have an actuation assembly to move the wing tip device.

Abstract: A wing assembly for an aircraft is disclosed including a wing and a wing tip device at the tip of the wing, wherein the wing tip device is moveable between a flight configuration and a ground configuration. The wing has a spar extension which extends spanwise away from a distal end of the wing, the spar extension having a first end portion fixed in the wing and a second end portion which, in the flight configuration, is positioned in the wing tip device such that, in the flight configuration, the spar extension transmits flight loads between the wing tip device and flight-load bearing structure in the wing. The wing assembly may have an actuation assembly to move the wing tip device.

Abstract: A small to mid-scale liquefied natural gas production system and method is provided. The disclosed liquefied natural gas production system employs a nitrogen-based refrigerant, at least one heat exchanger, three turbine/expanders and two or more refrigerant compression stages. The expansion ratio of one turbine/expander is appreciably lower than the expansion ratio of the other turbine/expanders such that the temperature of the exhaust stream from the turbine/expander with the lower expansion ratio is above the critical point temperature of the compressed natural gas containing feed stream but colder than ?15° C.

Abstract: A small to mid-scale liquefied natural gas production system and method is provided. The disclosed liquefied natural gas production system employs a nitrogen-based refrigerant, at least one heat exchanger, three turbine/expanders and two or more refrigerant compression stages. The expansion ratio of one turbine/expander is appreciably lower than the expansion ratio of the other turbine/expanders such that the temperature of the exhaust stream from the turbine/expander with the lower expansion ratio is above the critical point temperature of the compressed natural gas feed stream but colder than ?15° C.

Abstract: A small to mid-scale liquefied natural gas production system and method is provided. The disclosed liquefied natural gas production system employs a nitrogen-based refrigerant, at least one heat exchanger, three turbine/expanders and two or more refrigerant compression stages. The expansion ratio of one turbine/expander is appreciably lower than the expansion ratio of the other turbine/expanders such that the temperature of the exhaust stream from the turbine/expander with the lower expansion ratio is above the critical point temperature of the compressed natural gas containing feed stream but colder than -15° C.