Abstract: An inerting system, for instance an aircraft enclosure inerting system, is configured to separate an inlet air flow into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system has a vortex tube with a vortex chamber in which the inlet air flow is separated into the NEA and the OEA. The inlet air flow enters the vortex chamber through an inlet passage which intersects the vortex chamber at a chamber inlet aperture. A warming device of the inerting system warms the inlet passage or the inlet air flow before the inlet air flow gets to the chamber inlet aperture.

Abstract: A fuel mixing assembly is disclosed including a fuel vessel, such as a pipe for conveying flow of a first fuel, and a second-fuel conduit for conveying flow of, for example an additive, into the fuel vessel. The fuel mixing assembly further includes a vortex generator, the vortex generator is configured to generate vortices to mix the first fuel and the additive. The additive may be released from an outlet in the vortex generator.

Abstract: A vortex tube assembly for an aircraft enclosure inerting system has a plenum chamber and a swirl generator which has an inlet passage that allows air in the plenum chamber to enter a vortex chamber whereupon the air can be centrifugally separated into nitrogen enriched air (NEA) and oxygen enriched air (OEA). A throttle pin is positioned within the inlet passage, an outer surface of the throttle pin and an inner surface of the inlet passage co-operatively defining a flow path for air to enter the vortex chamber from the plenum chamber. The throttle pin is movable between a restrictive position and a permissive position, with the flow path being more constricted when the throttle pin is in the restrictive position than when the throttle pin is in the permissive position. The throttle pin is biased to the permissive position and movable to the restrictive position against this bias.

Abstract: An inerting system is provided with a vortex tube for separating air into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system has a warming device which warms NEA as it flows between an NEA outlet of the vortex tube and an NEA port of the inerting system. A method is also provided of supplying conditioned NEA to an enclosure, in which air is centrifugally separated into NEA and OEA in a vortex tube and the NEA is warmed so as to produce the conditioned NEA.

Abstract: A method of clearing a swirl generator of a vortex tube for an aircraft enclosure inerting system. The vortex tube has an inlet chamber and a vortex chamber which can receive air from the inlet chamber via flow paths in the swirl generator. The method comprises operating the vortex tube in a foreign matter clearance mode in which a reversed flow of gas is passed from the vortex chamber into the inlet chamber through the flow paths and dislodges accumulated foreign matter therefrom. Dislodged foreign matter is then exhausted from the vortex tube then the vortex tube is operated in a normal mode of operation.

Abstract: An inerting system has an inerting apparatus which receives an inlet air flow and separates it into nitrogen enriched air and oxygen enriched air. The inerting system also has an oxygen concentration sensor and a controller connected to the oxygen concentration sensor. The controller adjusts operation of the inerting system during use, based at least in part on feedback received from the oxygen concentration sensor.

Abstract: A cover for covering an access port of a fuel storage structure of an aircraft, the access port is configured to allow a human operator to access an interior of a first container of the fuel storage structure. The cover comprises an inlet port configured to interface with and receive fuel from an aircraft refueling apparatus, and an outlet port fluidically connectable to the inlet port and operable to provide the fuel received at the inlet port to the interior of the first container when the cover is arranged to cover the access port.

Abstract: Disclosed is an aircraft structure comprising at least one aircraft structural element defining a volume; a fuel-handling component arranged within the volume and configured to handle a fuel; a purging system comprising an inlet and an outlet, the purging system configured to provide a flow of purge gas from the inlet, through the volume, to the outlet, to thereby purge leaked fuel from the volume; and a flow guide member formed of a reticulated foam, arranged within the volume and externally to the fuel-handling component, and configured to guide the flow of purge gas within the volume. An aircraft comprising the aircraft structure is also disclosed.

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 method of fabricating a semiconductor device includes creating a device model of a drain extended transistor with a biased field plate, simulating performance of the drain extended transistor using the device model, adjusting the device model based on the simulation to create an adjusted device model to improve a figure of merit, and creating a circuit model of the drain extended transistor based on the adjusted device model. A semiconductor device includes a drain extended transistor having a field relief dielectric layer over a drain drift region, and a biased field plate over the field relief dielectric layer where a position and bias voltage of the field plate are determined by adjusting a device model of the drain extended transistor based on simulated performance of the drain extended transistor using the device model.

Abstract: Disclosed is an aircraft structure comprising at least one aircraft structural element defining a volume; a fuel-handling component arranged within the volume and configured to handle a fuel; a purging system comprising an inlet and an outlet, the purging system configured to provide a flow of purge gas from the inlet, through the volume, to the outlet, to thereby purge leaked fuel from the volume; and a flow guide member formed of a reticulated foam, arranged within the volume and externally to the fuel-handling component, and configured to guide the flow of purge gas within the volume. An aircraft comprising the aircraft structure is also disclosed.

Abstract: Disclosed is an aircraft structure comprising: at least one aircraft structural element defining a volume; a fuel distribution component, arranged within the volume, configured to hold fuel internally and transport held fuel through the volume; and at least one packing element formed of a reticulated foam, arranged within the volume, and at least partially surrounding the fuel distribution component. An aircraft comprising the aircraft structure is also disclosed.

Abstract: A fuel line terminating in a refuel connector is used to fuel or defuel an aircraft, for example with liquid hydrogen. A supply of nitrogen housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line to supply nitrogen into the fuel line, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line. The aircraft supply of nitrogen is also used to supply inert gas, via a gas line, to the Ground Support Equipment refuelling or defuelling the aircraft. This can provide redundancy for the Ground Support Equipment's systems, and may allow the aircraft to operate at less well-equipped airports.

Abstract: An aircraft enclosure inerting system has an inerting apparatus which receives air from an inlet, separates that air into nitrogen enriched air to be delivered to one or more enclosures of the aircraft, and oxygen enriched air. The inerting apparatus comprises at least first and second air separators. The first and second air separators are configured differently to one another. In some embodiments one of the air separators is a vortex tube and the other is a membrane-based air separation module. In some embodiments the inerting apparatus has at least two vortex tubes which are configured differently to one another.

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: A fuel line, terminating in a refuel connector, is used to fuel/defuel an aircraft, for example with liquid hydrogen. A barrier is disposed around the area where the refuel connector connects to an aircraft fuel port, and is sealed against the aircraft wing with a seal. A gas line runs generally parallel to the aircraft fuel line, and supplies inert gas, for example nitrogen, into the volume defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that area is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the fuel line structure.

Abstract: The disclosure is directed to a fuel line terminating in a refuel connector is used to fuel (or defuel) an aircraft, for example with liquid hydrogen. A barrier is deployed around the area where the refuel connector connects to an aircraft fuel port. A gas line supplies inert gas from a supply of gas, for example nitrogen, into the area defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that volume is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the refuel connector. The barrier, the gas supply, and/or the outlets for the inert gas to be supplied through are provided by a part of the aircraft.

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: 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.