Abstract: An apparatus and method for detecting current imbalance between two or more electrical energy distribution elements of an electrical energy distribution network are disclosed. Each of a plurality of temperature sensors are implemented by a temperature sensing section of an optical fiber arranged to produce, in response to an optical input signal, an optical output signal indicative of the temperature of the temperature sensing section. First and second temperature sensors of the plurality are in thermal contact with first and second electrical energy distribution elements, respectively, to determine first and second temperature characteristics thereof based on the respective output signals. A current imbalance between the first and second elements is detected based on a comparison of the first temperature characteristic with the second temperature characteristic.

Abstract: A fire sensor, fire sensing apparatus and a fire sensing system are disclosed. The fire sensor includes a layer of fibers arranged to cross one another at intersections. The fibers have an electromagnetic property which is changeable upon contact with fire and they are individually connectible to a detector of fire sensing apparatus to detect any change in the electromagnetic property. A change in electromagnetic property detected at any intersection of two fibers will indicate a fire at the location of that intersection. A movement of that location across the sensor will indicate the direction of travel of the fire. The sensing system is capable of sending alerts and extinguishing the fire.

Abstract: A hydrogen storage system comprises a hydrogen tank and a system for controlling hydrogen evaporation in the hydrogen tank. This control system comprises a hydrogen discharge pipe connected to the hydrogen tank, on the one hand, and to a controllable valve, on the other hand, as well as a processing unit configured to control the valve as a function of the pressure in the tank. The hydrogen storage system further comprises a fuel cell permanently connected to the hydrogen tank and the processing unit being electrically powered by the fuel cell.

Abstract: A method and system for estimating an angular deviation from a reference guidance axis, a position and a velocity of an aircraft. The system includes an offset collection module for collecting an offset measured by a measurement module, a position vector collection module for collecting a position vector measured by a position vector measurement module, a velocity vector collection module, a module for estimating the angular deviation of a reference guidance axis with respect to the approach axis towards the runway, for estimating the position of the aircraft with respect to the runway and for estimating the velocity of the aircraft with respect to the runway.

Abstract: A permanent magnet material is based on a manganese-aluminum alloy which further includes scandium. A method for producing such a permanent magnet material as well as the use of the permanent magnet material for producing a permanent magnet and for producing an electric motor and/or an electric power generating device are also described. Moreover, an electric motor including the permanent magnet material, an electric power generating device including the permanent magnet material, and an aircraft including the permanent magnet material or the electric motor or the electric power generating device are also described.

Abstract: A removable barrier and an aircraft including such a removable barrier. The barrier including a panel configured to block at least partly an opening delimited by a frame, a plurality of straps each connected to the panel and each having first and second ends, for each strap, a first connection configured to connect the first end of the strap and a first edge of the frame at least temporarily, a second connection configured to connect the second end of the strap and a second edge of the frame at least temporarily, at least one folded overlength at the level of at least one of the first and second ends of the strap, at least one breakable connection keeping the overlength folded.

Abstract: An apparatus configured to determine the pressure of an aircraft tire at a reference temperature. The apparatus includes a processing system configured to: obtain a measured tire pressure and a measured temperature associated with the measured tire pressure; and determine a tire pressure at the reference temperature by adjusting the measured tire pressure using a predetermined temperature characteristic, a square root of the measured temperature and a square root of the reference temperature. The predetermined temperature characteristic is a gradient of the relationship between square root of temperature and tire pressure.

Abstract: A reusable seal including an antenna, an opening sensor to sense the opening of a volume to be monitored and an electronic device coupled to the antenna and configured to communicate with a reader via the antenna. The electronic device is supplied with power only by the antenna when a reader is proximate to the antenna. The seal has a memory that may assume an active state or an inactive state. The seal is configured such that the memory may be activated only by the electronic device when the device is supplied with power to store an intact seal state in the memory, and the memory may be deactivated at any time when the opening sensor is actuated to store a non-intact seal state in the memory. The seal is configured to respond to a request from a reader regarding its state according to the memory state.

Abstract: An electricity production system for an aircraft comprising a fuel cell, with an anode and a cathode, supplying an electric motor, a first feed pipe between the anode and a hydrogen source, a compressor, a second feed pipe between the inlet of the compressor and an oxygen source, a first transfer pipe between the outlet of the compressor and the cathode, a valve, an upstream pipe between the outlet of the compressor and the valve, a downstream pipe between the valve and an air outlet, and a controller which controls the position of the valve and the flow rate of the compressor. Such an electricity production system thus provides better control of the air flow supplied to the fuel cell on the basis of the electrical power required for the electric motor providing propulsion.

Abstract: A tooling to enable variation in radius of molded continuous fiber reinforced polymer curved components which includes a first tooling surface formed on a first tooling member which may be formed of sprung material, a second tooling surface formed on a second tooling member which may be formed of sprung material. The first tooling surface and the second tooling surface are positioned to lie one over the other to form a gap therebetween for receiving a supply of continuous fiber reinforced polymer. The first tooling surface and the second tooling surface are movable towards and away from each other to modify the size of the gap therebetween and thereby modify the amount of compression applied by the first and second tooling surfaces on the continuous fiber reinforced polymer positioned therebetween. A mechanism is engaged with the first tooling member to modify a curvature of the first tooling surface.

Abstract: A bumper for a vehicle, comprising at least one part made of resilient material, having a curved front portion forming an inner cavity. The front portion has apertures enabling the cavity to be put into communication with the exterior of the resilient part. At least one marking fluid cell is provided inside the cavity. A fastener is provided to fasten the one part to the vehicle.

Abstract: A process of joining a wing to an aircraft fuselage comprising the steps of: mapping the wing root of the wing, mapping the center-wing-box (CWB) of the aircraft fuselage, determining the position to provide the hole pattern on the CWB, providing the holes on the CWB, and attaching the wing root to the CWB. Primary and secondary templates with corresponding hole patterns may be used in combination with targets and laser trackers to implement the process. The hole pattern of the wing root can therefore be duplicated on the CWB at a position such that when the wings are joined to the fuselage, the aircraft will have optimum flight performance and dynamic symmetry. A predictive fit is thus provided, based on virtual representation and analysis, and advantageously permits the hole pattern to be provided without requiring the CWB and wing root to be brought together.

Abstract: An apparatus for an aircraft having one or more aircraft wheel brakes, and a brake wear sensor configured to measure a wear state of a brake of the one or more aircraft wheel brakes, is disclosed. The apparatus includes a processor configured to determine a wear relationship between a wear state of the brake and a number of use cycles of the brake, determine a predicted wear state of the brake based on the wear relationship; determine a number of future use cycles of the brake based on a predicted condition of the brake, the predicted condition comprising the predicted wear state of the brake; and provide an indication of the determined number of the future use cycles to ground crew and/or a pilot of the aircraft, wherein the number of future use cycles is the number of use cycles for which the brake is allowed to be used, and a use cycle comprises all uses of the brake relating to a flight undertaken by the aircraft.

Abstract: A method for managing the offtake of power produced by an auxiliary power unit of an aircraft. The method comprises a step of calculating a maximum capacity for offtake of mechanical power that the auxiliary power unit can provide to the aircraft, a step of determining an actual offtake of mechanical power taken off by a first mechanical power offtake system of the auxiliary power unit, a step of comparing the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, a step of optimizing the offtake of mechanical power which step, based on the comparison of the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, determines at least one corrective action. A device for managing the offtake of power produced by an auxiliary power unit of an aircraft and an aircraft including such a device are provided.

Abstract: A vehicle bumper comprising at least one part made of resilient material, in the interior of which there is provided at least one marking fluid cell with an opening to the exterior. The opening is closed by a closure device which, under the effect of a pressure applied with a determined intensity, can open up the opening, allowing the marking fluid to access the exterior of the cell through which the marking fluid can flow, and also comprising a securing element configured to secure the at least one part on the vehicle.

Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Abstract: A Yagi-Uda monopolar antenna configured to be mounted on the conductive surface of a vehicle, especially an aircraft. The antenna comprises: a radiating element, taking the form of a conductive plate, for example one having the shape of a disc, which plate is equipped with a return conductor; a reflecting element; and at least one directing element taking the form of a monopole that is folded on itself. The various elements are mounted on a substantially planar surface such as the skin of the fuselage of an aircraft. The antenna simultaneously has a wide operating band, a good compactness and a good directivity. It may especially serve as joint antenna for a plurality of air-ground communication systems of an aircraft.

Abstract: An aircraft includes comprises toilet that includes a protection device configured to contain effects of a malicious device, in order to protect both a fuselage of the aircraft and passengers of the aircraft against the effects of the malicious device.

Abstract: A composite panel having a plurality of carbon plies, a perforated metallic foil comprising several apertures and being directly secured to the plurality of carbon plies, and a protective layer made from resin reinforced with fibers which is secured to the metallic foil. The perforated metallic foil is embedded in the protective layer through its apertures. A free surface of the protective layer forms a top side of the composite panel. The thickness of the protective layer between the top side of the composite panel and the perforated metallic foil is at least 15 micrometers and the perforated metallic foil has a thickness of not more than 30 micrometers. The plurality of apertures in the aggregate defines an open area of not more than 40% of the surface area and a maximum distance between two opposed points in a perimeter of an aperture is equal to or less than 3 mm.

Abstract: A fuselage assembly for an aircraft including a stringer extending longitudinally along the fuselage. The stringer defines a fluid channel. The fluid channel is configured to form at least part of a distribution duct of a cabin air distribution system.