Abstract: A method of determining a status of a tyre monitoring device is disclosed. The tyre monitoring device includes a counter initiated on a first use of the tyre monitoring device on a wheel and the method includes: determining a current value of the counter; determining a status of the tyre monitoring device based on the current value of the counter; and providing an indication based on the determined status. In some examples, the status is a remaining service lifetime and the indication may be a replacement notification. A method of cross-checking data between tyre monitoring devices is also disclosed. The method includes receiving data from a plurality of tyre monitoring devices associated with respective tyres of a same vehicle; comparing the received data from different ones of the plurality of tyre monitoring devices; determining inconsistent data associated with at least one of the plurality of tyre monitoring devices based on the comparison; and providing an indication of the inconsistent data.

Abstract: A leading-edge component for an aircraft includes at least a part of a flow body having a front skin and a rib. The front skin comprises a top section, a bottom section and a leading edge arranged therebetween. The rib extends from the bottom section to the top section. The rib comprises a flange that at least partially surrounds the rib. The flange is attached to an inner side of the front skin. The at least one peripheral surface extends from the contact surface inwardly into the flow body and away from the inner side of the front skin or encloses a weakened connection region with the contact surface for bending inwardly into the flow body upon an impact onto the front skin on or adjacent to the at least one peripheral surface.

Abstract: An expansion tank system for a liquid cooling system includes a first chamber for receiving a coolant, a second chamber for pressurized gas, a first gas conveying device for conveying gas from the first to the second chamber, a second gas conveying device for conveying gas from the second to the first chamber, a first pressure sensor in fluid communication with the first chamber, and a control unit connected to the first gas conveying device, the second gas conveying device and the first pressure sensor for controlling the second conveying device to selectively convey gas from the second to the first chamber if a pressure measured through the first pressure sensor is below a predefined first threshold value, and for controlling the first conveying device to convey gas from the first to the second chamber if a pressure measured through the first pressure sensor is above a second threshold value.

Abstract: An aircraft glazing unit including a body of transparent material and at least one subsurface thickness indicator at a predetermined depth within the material. The provision of a subsurface thickness indicator allows for the unit to be re-polished to remove erosion, whilst providing a visual indicator to ground crew of the remaining thickness of material in the unit. In this way, the service lifetime of the glazing unit can be extended.

Abstract: A barrel nut retainer for retaining a barrel nut in a bore of a component is disclosed having a body adapted to fit within a bore and extending between a first end and a second end, and wherein the body has an aperture between the first end and second end configured to receive a barrel nut, and a head portion at the first end of the body, the head portion adapted to sit over an open end of the bore.

Abstract: A piccolo tube for de-icing an airfoil structure of an aircraft is disclosed having a shape extending in a longitudinal direction and is configured for installation in an airfoil structure of an aircraft in the longitudinal direction of the airfoil structure. The piccolo tube includes a connector element for receiving heated air from a supply source, and a longitudinally extending air duct having a plurality of outlet openings arranged along the air duct, for supplying and distributing the heated air along the inner side of the airfoil structure. The piccolo tube is curved and its curvature is adapted to a curvature of the airfoil structure in its longitudinal direction. A de-icing system includes the piccolo tube and a supply source for supplying heated air to the piccolo tube. An airfoil structure includes the piccolo tube and/or the de-icing system.

Abstract: A movable flow body device for an aircraft including an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a second position and a third mechanical interface in a third position. The first mechanical interface may be a master interface arranged in a central region, while the second and third mechanical interfaces are slave interfaces. Preferably, in the outboard position, a link plate between a support lever and a support rib of the flow body is inverted compared to the further inboard mechanical interface, which allows for supporting slimmer and longer flow bodies in the outboard region and providing a rigging hinge line through the whole flow body.

Abstract: A system includes a reception unit to receive current flight data of the aircraft and current meteorological data, a data processing unit to perform an iterative computation to determine, as a function at least of a set of predetermined rules, of a set of constraints and of current values including current meteorological data, an optimal flight trajectory making it possible to generate a dissipation of the energy of the aircraft to bring it, at a stabilized final position, into a final energy state with a minimum ground distance, the optimal flight trajectory defining positions at which actions must be implemented on the aircraft, and a data transmission unit to transmit at least the minimum distance to at least one user system.

Abstract: A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p?1 inputs, receiving as input distinct subsets of 2×p?1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p?1 inputs and delivering as output the two intermediate values.

Abstract: A tank suitable for storing a product at a cryogenic temperature, including a fluid tight interior barrier, a fluid tight exterior barrier, surrounding the first interior barrier, an intermediary volume interposed between the interior and exterior barriers and at least one insulating layer positioned in the intermediary volume and including at least one thermal insulation mat, with very low thermal conductivity. The intermediary volume contains microspheres outside of the thermal insulation mats and has an enhanced level of vacuum. This solution makes it possible to maintain satisfactory performance in terms of thermal insulation even in the event of a loss of vacuum in the intermediary volume.

Abstract: A method for managing access to a shared resource in an electronic system including a control unit and the shared resource. The control unit is intended to execute applications that are candidates for access to the shared resource. The method uses a calendar of periods of equal duration, each assigned to just one of the applications, to define a temporal distribution of access to the shared resource, and penalty indices associated with each of the applications. The method includes steps for conditionally processing the access requests transmitted by the applications according to their penalty indices. Thus, each application is prevented from accessing the shared resource when the quota assigned thereto is reached, which makes it possible to limit the encroachment of an application that is executed on the access quotas for accessing the resource that are assigned to the other applications.

Abstract: An actuator arrangement for a fixed leading edge member of an aircraft wing. The fixed leading edge member has an inner cavity defined by the outer skin and ribs. The actuator arrangement comprises at least one geared rotary actuator which moves relative to the other parts along a circular arc section during extending and retracting of the high-lift device between a fully retracted position and a fully extended position. In the fully retracted position, the actuator is predominantly accommodated within the inner cavity and in the extended position the actuator is predominantly positioned outside the inner cavity, preferably protruding through a D-nose cut-out.

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

Abstract: A method for depressurizing a cabin of an aircraft on the ground from the outer side of the aircraft using a depressurizing system including a venting valve which can be actuated between open and closed positions by means of a shutter and which is connected in fluid terms to a vacuum pump and to a pressure tap port of the aircraft which is connected to a protection valve against excess pressure in the cabin. The method includes fluidly connecting the venting valve to the pressure tap port, the shutter being in the open position, moving the shutter to the closed position thereof and activating the vacuum pump to generate a reduced pressure in the region of the pressure tap port.

Abstract: A method of removing hydraulic fluid from an aircraft hydraulic system is disclosed including a hydraulically actuated mechanism that is actuated by an electrohydraulic servo valve, a hydraulic fluid port through which hydraulic fluid can escape, and a hydraulic fuse with a closed state and an open state between the electrohydraulic servo valve and the hydraulic fluid port. The hydraulic fluid port is opened, and then the activation of the electrohydraulic servo valve is controlled to force hydraulic fluid to escape from the hydraulic system via the hydraulic fluid port, the control being so that the hydraulic fuse does not enter and remain in the closed state.

Abstract: A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.

Abstract: The enhanced flight vision system of an aircraft comprises an image acquisition system provided to acquire images of an outside environment of the aircraft, and a display system configured to allow information to be displayed on a display unit overlayed with the outside environment of the aircraft. The display system is configured to receive images produced by the image acquisition system and to display these images on the display unit. The image acquisition system is configured to associate ancillary information with at least a part of the images produced and the display system is configured to check the integrity of an image received from the image acquisition system, based on the ancillary information associated with that image; and in the absence of integrity, deactivate the display on the display unit of at least the image received from the image acquisition system.

Abstract: An aircraft landing gear support (1) including: a support member (such as a landing gear rib (2)) and a plurality of pintle supports (5, 7, 8) (typically in the form of lugs) which form a pintle support arrangement for holding a pintle on which a landing gear assembly may be rotatably supported. The lugs are removably attached to the gear rib.

Abstract: A textile fiber-composite material precursor and method for producing a component from fiber-composite material. Aircraft components can be produced from polymer fiber-composite materials, a matrix of which can be a high-performance plastics material such as polyether ketone ketone wherein a reinforcement of a non-crimp fabric of carbon fibers is embedded. Large-area non-crimp fabrics and large-area polymer films can be consolidated while being heated and pressed forming simple components. The flexible textile fiber-composite material precursor includes a stack of woven-fabric tiers from a polymer and of non-crimp fabric tiers from carbon fibers. Since both components are capable of draping, the fiber-composite material precursor can be deposited over a large area on curved shape-imparting surfaces and subsequently be consolidated under pressure and heated to form the fiber-composite material.

Abstract: Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.