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: This disclosure enables various technologies that can (1) learn new synonyms for a given concept without manual curation techniques, (2) relate (e.g., map) some, many, most, or all raw named entity recognition outputs (e.g., “United States”, “United States of America”) to ontological concepts (e.g., ISO-3166 country code: “USA”), (3) account for false positives from a prior named entity recognition process, or (4) aggregate some, many, most, or all named entity recognition results from machine learning or rules based approaches to provide a best of breed hybrid approach (e.g., synergistic effect).

Abstract: An aircraft engine incudes: a catalyst, e.g. platinum, applied to turbine blades (580c, 590c) and/or to a catalytic grid downstream of the engine's combustion chamber. An exhaust fluid additive injection system is incorporated upstream of the catalyst via a line 560, in a stator blade within the engine. The catalyst is used to reduce NOx emissions from the engine by a Selective Catalytic Reduction reaction.

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: This disclosure enables various technologies that can (1) learn new synonyms for a given concept without manual curation techniques, (2) relate (e.g., map) some, many, most, or all raw named entity recognition outputs (e.g., “United States”, “United States of America”) to ontological concepts (e.g., ISO-3166 country code: “USA”), (3) account for false positives from a prior named entity recognition process, or (4) aggregate some, many, most, or all named entity recognition results from machine learning or rules based approaches to provide a best of breed hybrid approach (e.g., synergistic effect).

Abstract: This disclosure enables various technologies that can (1) learn new synonyms for a given concept without manual curation techniques, (2) relate (e.g., map) some, many, most, or all raw named entity recognition outputs (e.g., “United States”, “United States of America”) to ontological concepts (e.g., ISO-3166 country code: “USA”), (3) account for false positives from a prior named entity recognition process, or (4) aggregate some, many, most, or all named entity recognition results from machine learning or rules based approaches to provide a best of breed hybrid approach (e.g., synergistic effect).

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 includes an active drag control system such as a Laminar Flow Control (LFC) system having a port LFC apparatus and a starboard LFC apparatus. The aircraft has a control system to test how efficiently the LFC system is working by differentially operating the port LFC apparatus and the starboard LFC apparatus, for example by deactivating either LFC apparatus, and measuring the effect on the direction of flight of the aircraft. The control system also can change the direction of the aircraft, and trim the aircraft, by differentially operating the port LFC apparatus and the starboard LFC apparatus.

Abstract: A system and method for liquefaction of natural gas using two distinct refrigeration circuits having compositionally different working fluids and operating at different temperature levels is provided. The turbomachinery associated with the liquefaction system are driven by a single three-pinion or four-pinion integral gear machine with customized pairing arrangements. The system and method of natural gas liquefaction further includes the conditioning of a lower pressure natural gas containing feed stream to produce a purified, compressed natural gas stream at a pressure equal to or above the critical pressure of natural gas and substantially free of heavy hydrocarbons to be liquefied.

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: This disclosure enables various technologies that can (1) learn new synonyms for a given concept without manual curation techniques, (2) relate (e.g., map) some, many, most, or all raw named entity recognition outputs (e.g., “United States”, “United States of America”) to ontological concepts (e.g., ISO-3166 country code: “USA”), (3) account for false positives from a prior named entity recognition process, or (4) aggregate some, many, most, or all named entity recognition results from machine learning or rules based approaches to provide a best of breed hybrid approach (e.g., synergistic effect).

Abstract: An apparatus is described and includes a packet reordering engine (PRE) for reordering data packets stored in a packet buffer at locations identified by buffer descriptors (BD). The PRE includes a BD fetch manager for fetching BDs associated with the stored data packets; a header decoder module for fetching the header portion for the stored data packets associated with the fetched BDs; a reorder module for receiving the fetched BDs and the fetched header portions and storing the fetched BD associated with the data packet in a slot of the reorder buffer; and a buffer processor configured to receive BDs from the reorder module in an order indicated by the header information of the data packets associate with the BDs and to fetch the payloads of the data packets with which the received BDs are associated from the packet buffer.

Abstract: Systems and methods for converting images, such as JPEG images. Decoded image data is produced in block format having minimum coded units (MCUs). The blocks each include a square of pixels and are stored in linear format in memory. A block to burst converter is provided that receives a set of image blocks, stores partial rows of a frame locally, and then writes out each partial row in a burst of raster blocks. The systems and methods provided herein reduce local memory use by orders of magnitude while also reducing system latency.

Abstract: A method is provided for determining a unique identifier of a device, the device 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: 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 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: 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: 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: 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).