Abstract: An aircraft wing (2) including a main wing (3) and a wing tip device (4) at the tip of the main wing (3), wherein the wing tip device (4) has a variation of leading edge droop with respect to unrolled span-wise position such that flow separation on the wing tip device (4) first occurs in an outboard region (O) of the wing tip device (4). The leading edge droop of the wing tip device (4) may be a maximum in an outboard region (O) of the wing tip device.

Abstract: An actuating system for pivoting a wing tip section (13) about a fixed wing base section (11), and including a heating arrangement (33) positioned and adapted to be operable to heat at least one portion of an actuating arrangement (23) that pivots the wing tip section such that at least for ambient temperatures below a predetermined temperature the required work to be effected by the actuator (25) when moving the second coupling part (31) between the first position and the second position is lower than without heating the at least one portion.

Abstract: A process is proposed for producing a component, in which at least one first two-dimensional laid scrim is produced from a fibre composite material having a constant thickness, an outer face and an inner face. At least one second two-dimensional laid scrim is arranged with respect to the first two-dimensional laid scrim and then consolidated. The first two-dimensional laid scrim can be provided in a continuous, efficient production process, which increases speed and lowers costs.

Abstract: A flight control surface with an actuator with an aerodynamic fairing for a swept aircraft wing. The swept aircraft wing includes a movable flight control surface with a hinge line non-perpendicular to the line of flight of the aircraft, and an actuator arm configured to actuate the flight control surface. The actuator arm includes a longitudinal axis substantially aligned with the line of flight, the actuator arm extending at least partially from an outer surface of the aircraft wing, and a fairing arranged on the outer surface of the aircraft wing to at least partially cover the actuator arm. Aligning the actuator arm with the line of flight of the aircraft may allow for an improved fairing to be provided.

Abstract: An inerting system and method for an aircraft includes an inert gas generation apparatus, an air supply line, a compressor and an inert gas line. The compressor supplies the inert gas generation apparatus with air from the air supply line at a pressure necessary for operation of the inert gas generation apparatus. The inert gas line carries the inert gas produced by the inert gas generation apparatus on to an inert gas consumer. The air supply line is connected to an exhaust air system of the aircraft. A method for supplying an inert gas in an aircraft includes tapping of air from an exhaust air system of the aircraft, compression of the tapped air, and production of inert gas in an inert gas generation apparatus from the compressed air. An aircraft is disclosed in which such an inerting system is arranged and/or used.

Abstract: A method for manufacturing a part layer-upon-layer using Additive Manufacturing technology, the method including: printing the part together with an elastomeric enclosure shaped thereto leaving a gap free of material therebetween, the elastomeric enclosure including at least one opening; heating the ensemble of the printed part and elastomeric enclosure or keeping an operating printing temperature; applying vacuum by the at least one opening of the elastomeric enclosure so that the elastomeric enclosure deflates thus exerting pressure to the printed part; and maintaining the printed part under vacuum and heat during a predefined time.

Abstract: Systems for securing fixtures to the floor of a transportation vehicle. The securing system has a simplified structure comprising a securing device with two C-profiles comprising a web extending between a top plate and a bottom plate, the profiles being joined by an omega-shape fishplate. Vertical lateral walls formed by the webs of the profiles are perforated.

Abstract: An actuation unit (15) for actuating a foldable wing tip portion (9) of a wing (3) for an aircraft (1). The actuation unit (15) includes a track (25) configured to be mounted to a fixed wing (5), a carriage (27) configured to engage the track (25) for guided movement along the track (25), and configured to be coupled to a drive unit (31) for driving the carriage (27) along the track (25), and a link (29) configured to be coupled to the carriage (27) and configured to be coupled to a foldable wing tip portion (9).

Abstract: A platform for unmanned traffic management (UTM) may include a compute system and infrastructure that standardizes and controls aviation data transmitted between service providers, where each service is abstracted from the platform through a service wrapper that enforces the preset data standards. The service wrappers enforce restrictions on the performance and configuration of data from the service provider. The service wrappers are customized to respective services (such as tracking, terrain, or weather), but provide a standard point of interface, security, and trust between the platform and any services directed to provide a similar function. Upon the request of a user or service providers to obtain aviation data, the UTM platform selects a service providing that aviation data, and provides connection data to the user while protecting the security and integrity of the data.

Abstract: A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a first hinge (11) rotatable about a first hinge axis (13) between an extended position (15) and a folded position (17), and an actuation unit (19) arranged at the fixed wing (5) and coupled to the foldable wing tip portion (9) via a linkage (21) including a first link element (23) and a second link element (25), wherein the first link element (23) is mounted to a rotatable output (27) of the actuation unit (19) and is rotatably coupled to the second link element (25) via a second hinge (29), and wherein the second link element (25) is rotatably coupled to the foldable wing tip portion (9) via a third hinge (31).

Abstract: Methods and systems for detection of cyberattacks in onboard systems of aircraft. Measurements carried out on these onboard systems are correlated, in case of doubt of one of the measurements, to validate the doubt, (and therefore a cyberattack) or to avert the risk. The correlation can be understood as a coming into correspondence of two or more elements/facts (for example measurements or acquired values) which makes it possible to highlight if there is a dependence of one upon the other and thus to justify modifications of one by those of the other. The correlation, preferably temporal, between identification of a suspect measurement and one or more other (quasi)simultaneous measurements allows dynamic detection, in real time, of the cyberattacks, whether they be already known or not. Thus, there is no dependence on a static protection of the onboard systems developed on the a priori knowledge of the existing cyberattacks alone.

Abstract: Method and system for merging measurements of flight parameters of an aircraft. The system is for merging measurements of flight parameters of an aircraft, linked to one another by at least one equation, and includes at least one acquisition module for acquiring at least one measurement of flight parameters, a scoring module for attributing a first validity score to the equations by checking whether the measurement or measurements of flight parameters are a solution or solutions of the equation or equations, a scoring module for attributing a second validity score to failure scenarios involving one or more acquisition modules from the first validity scores, a determination module for determining the validity of the measurements of flight parameters from the second validity scores, consolidation module for consolidating the measurements of flight parameters, a transmission module for transmitting the consolidated measurements of flight parameters to a user device.

Abstract: An air inlet device for an air inlet of an aircraft. The air inlet device has air guide arrangements. An air guide arrangement has an inlet plate, an outlet plate, and pivot plates arranged therebetween. The outlet plate and the pivot plates can be rotated about a central axis of the air inlet device by adjustment rings, so that the air guide arrangement is transitioned from a linear state to a curved state, and vice versa. The air inlet device allows for selective switching between a state with low radar signature and a state with high performance of an engine.

Abstract: An oxygen supply system providing an adequate oxygen supply mode in an aircraft. A preventive oxygen supply system includes an oxygen source, a preventive oxygen dispensing unit connectable to the oxygen source, a cabin altitude detection device, and a preventive oxygen control device provide at least the following modes: a pre-wear mode providing no oxygen of the oxygen source to the preventive oxygen dispensing unit but normal cabin air; a pre-oxygenation mode providing a predetermined rate of oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for generating a pre-oxygenation condition of the user; and a decompression mode providing high concentrated oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for ensuring a minimum oxygenation of the user. The preventive oxygen control device automatically switches to the decompression mode in case a predetermined cabin altitude threshold is detected by the cabin altitude detection device.

Abstract: A device for fixing cabin side wall and cabin light paneling to a structural component of an aircraft and spacecraft includes: a structure holding component; and a cabin side wall holding component. The structure holding component has a surface for fixing the holding component to the structural component, and an adjustable surface for fixing the side wall holding component. The side wall holding component has an intermediate bracket and a side wall receiver for fixing cabin side wall paneling. The intermediate bracket is arranged between the adjustable fixing surface and the side wall receiver. The intermediate bracket has an intermediate guide element which guides the intermediate bracket, and the side wall receiver has a receiver guide element which guides the side wall receiver. The intermediate bracket has a fixing element for locking the intermediate bracket, and the side wall receiver has a fixing element for locking the side wall receiver.

Abstract: A system for synchronizing transceivers which includes a first and second plurality of transceivers. The first plurality of transceivers are arranged at fixed positions with respect to each other. One of the first plurality of transceivers is configured to transmit a first wideband signal. The second plurality of transceivers are arranged at fixed positions with respect to each other. Each of the second plurality of transceivers is configured to receive the first wideband signal and to generate a respective one of second wideband signals based on the respectively received first wideband signal modified by a respective one of offsets which differ from each other, and to transmit the respective one of second wideband signals. The one of the first plurality of transceivers is configured to receive the second wideband signals which form the basis for synchronizing one of the first plurality of transceivers with the second plurality of transceivers.

Abstract: An assembly constituting an acoustically absorbent material and including a first panel, a second panel pierced with holes, an intermediate panel pierced with through-holes and arranged between the first panel and the second panel, a first structure between the first panel and the intermediate panel and including first cages, a second structure between the second panel and the intermediate panel and including second cages, and for each through-hole of the intermediate panel, a tube opening out at the two ends thereof, where one of the ends of the tube is fixed to the intermediate panel at the through-hole, and where the other end of the tube is accommodated inside a first cage. Such an assembly makes it possible to obtain broad-band attenuation and is easy to manufacture.

Abstract: A fiber composite laying device for producing a fiber composite scrim for forming a fiber composite component has a laying head which is designed or configured to continuously supply a reinforcement fiber band, a compaction roller which is designed or configured to receive the supplied reinforcement fiber band, lay the band on a laying surface and press the band onto the laying surface at an average compaction pressure, and pressure sensors which are arranged on the compaction roller and are designed or configured to detect a local compaction pressure on the laid reinforcement fiber band.

Abstract: A method and device for optimizing tests of systems, in particular of an aircraft, including a first display module displaying a list of tests that can be executed by systems, a selection module allowing an operator to select a set of tests to be executed and communicate it to an optimization module which determines a sequence of tests representing an optimized execution of the set of tests to be executed, the sequence of tests being displayed by a second display module for an operator, a decision module generating either a first signal if the operator validates the sequence of tests, or a second signal if the operator cancels the sequence of tests, and a control module which, if the first signal is generated, commands the execution of the sequence of tests by each of the systems, and generates results of the execution thereof.

Abstract: An airfoil arrangement which allows an increased reliability and increased aerodynamic performance of airfoils. A catching bracket is provided which is mounted in a track device opening to reduce the area of the track device opening and, when there is a failure of at least one support roller, the catching bracket engages the track device.