Abstract: A method of landing an aircraft in which the aircraft receives information from a second aircraft via a direct aircraft-to-aircraft communication from the second aircraft to the aircraft; determines a landing plan of the aircraft based on the information; and lands the aircraft based on the landing plan. The use of a direct aircraft-to-aircraft communication (i.e. a communication from the second aircraft to the first aircraft which does not travel via an intermediary such as a land station, air traffic controller or satellite) makes the method reliable because such a communication is inherently secure and difficult to hack.

Abstract: A method of determining a status of a tyre monitoring device that includes a power supply. The method includes determining a value indicative of consumption of the power supply, determining a status of the tyre monitoring device based on the value indicative of consumption of the power supply, and providing an indication based on the determined status.

Abstract: A human and/or non-human cargo attachment device for a rotorcraft. The device comprises a mounting interface with a carrier device and an attachment that is rigidly mounted to the carrier device for attachment to a rotorcraft rope or cable. A device body is mounted to the carrier device. The device body has a stationary body section and a movable body section. The stationary body section is stationarily arranged on the carrier device and comprises a plurality of rotatable attachment hooks for attachment of human or non-human external cargo. The movable body section is movably arranged on the carrier device for enabling movements of the movable body section relative to the stationary body section between a locking position and a release position.

Abstract: An acoustic treatment panel includes at least one acoustically resistive layer, a reflective layer and at least one cellular structure interposed between the acoustically resistive layer and the reflective layer. The cellular structure includes cylindrical and identical main tubes which are closed at one end by the acoustically resistive layer and at the other end by the reflective layer, spacer zones between the main tubes, the spacer zones being sealed relative to one another, cutouts made at an end of certain main tubes, in contact with the reflective layer, and/or secondary tubes positioned in the main tubes and/or in the spacer zones, the cutouts and/or the secondary tubes being configured to generate acoustic cells of different dimensions from identical main tubes.

Abstract: A spark containment cap for enclosing an end of a fastener protruding from a structure, the enclosed body having a base and a cover portion, the cover portion extending from the base, the base providing an adhering surface for adhering the spark containment cap to a structure, and the base and the cover portion together forming a cavity within the enclosed body inside which the end of a fastener can be enclosed.

Abstract: A computer-implemented method of predicting tire pressure of a tire of an aircraft, the method including obtaining first data indicative of an inflation pressure of the tire, obtaining second data indicative of a brake temperature of a brake associated with an aircraft wheel to which the tire is mounted, obtaining third data indicative of a gas temperature of the tire, and obtaining fourth data indicative of one or more predicted operational conditions of the aircraft during a future time period. The method includes determining, based at least in part on the first, second, third and fourth data, predicted tire pressure characteristics of the tire during the future time period.

Abstract: An unmanned ground-based transport vehicle, UGV, includes a housing, having a base plate and at least one housing side wall substantially perpendicular to the base plate. Arranged in the housing is at least one wheel drive, which is coupled to at least one wheel. The wheel is arranged in a recess in the base plate. The UGV further includes sensors for sensing the environment of the UGV, and a controller for autonomous location and navigation of the UGV on the basis of sensing parameters of the sensors. The UGV includes at least one load-receiving element coupled to the housing side wall and extending outwards from the housing side wall, wherein the load-receiving element includes a load support surface for supporting an item with respect to a vertical direction which extends transverse to the base plate.

Abstract: A support for the maintenance of an aircraft radome comprising an annular element having a flat surface and from which extend at least three feet. The support comprising a plurality of articulated holding elements, for example articulated fittings, applying a lock function and each comprising a bearing surface on a surface portion of an aircraft radome, for example an interface fitting, when said radome is placed on said flat surface of said annular element.

Abstract: A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

Abstract: A freight container configured to fit in an aircraft cargo hold includes a floor element. First and second parallel side walls extend away from first and second opposite edges of the floor element base surface. A top wall, parallel to a floor element resting surface, extends between edges of the first and second side walls, which edges are remote from the first and second edges. A front wall extends between the first and second side walls from a base surface third edge to a top wall front edge. The front wall has a first front wall portion, extending from the base surface third edge at a first angle of at least 90° to the resting surface. The front wall has a second front wall portion, extending from the top wall front edge at a second angle of less than 180° and more than 90° to the top wall.

Abstract: A computer-implemented method of tire maintenance including: receiving data of a plurality of tire gas pressure measurements each measurement having an associated time; analyzing the received data to determine maintenance information, wherein the maintenance information comprises at least one of: an inflation event, a maximum pressure, a minimum pressure and a tire replacement event; and providing an indication based the determined maintenance information.

Abstract: A connector for a structurally integrated line system of a vehicle, having a first end portion, a second end portion and a connecting piece extending between the first end portion and the second end portion, wherein the first end portion has at least one contact face for arrangement on a structurally integrated line, wherein at least one of the at least one contact face has a cutout which is surrounded by a closed border, wherein the second end portion has a flange connection for connection to a pipe.

Abstract: A stiffener is disclosed including a core and a shell which surrounds the core. The shell is formed from a fibre material, and the core includes first and second battens arranged side by side, and a foam spacer between the battens. The stiffener extends in a lengthwise direction, and the battens and the foam spacer have respective lengths which extend in the lengthwise direction of the stiffener. The core is assembled with the spacer between the battens, then surrounded with the shell. The stiffener may be a stringer for an aircraft wing.

Abstract: A wing for an aircraft includes a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one of a fluid line, an electrical line, and a mechanical power transfer device attached inside or reaching into the wing box at least partially.

Abstract: An aircraft tank device for increasing a flight range and a wing area of an aircraft includes a fairing which is formed and configured to at least partly cover an aircraft wing-aircraft fuselage intersection, to store a fuel, and to provide a lifting function. An aircraft including such an aircraft tank device is also disclosed.

Abstract: A system comprising a connection device having a first shaft and a second shaft, the connection device comprising a free-wheel interposed between the first shaft and the second shaft that can only transmit engine torque from the first shaft to the second shaft when a motor mode is activated. The connection device comprises a coupler, the coupler being provided with a fusible section, the connection device comprising a dog clutch connection that can only transmit engine torque from the coupler to the first shaft when an electrical power generation mode is activated.

Abstract: The system includes a closing module removably fastened to one end of the articulated arm of the door with which a door leaf is articulated, a closing module removably fastened to a structure rigidly connected to the door frame and a locking device removably fastened to the articulated arm. The closing module is able to alternately pull the closing module towards itself to move the door leaf into the closed position, and to move the closing module away from itself to move the door leaf into the open position. The locking device allows the locking lever to be moved alternately into the unlocked position to unlock the door leaf and into the locked position to lock the door leaf. The system enables the door of the aircraft to be closed remotely.

Abstract: A primary structural assembly for an aircraft outside-skin heat exchanger, the assembly comprising an outer-skin portion which defines an outer shape of the aircraft and forms a portion of a hull of the aircraft, wherein the outer-skin portion comprises at least one recess, a thermal-transfer fluid connection which is designed to convey a thermal-transfer fluid into the recess, a component which closes the recess, and at least one retaining element which is arranged in or on the recess and is configured to hold the component closing the recess, in the recess. Further, an aircraft including such a primary structural assembly and a method for attaching the aircraft outside-skin heat exchanger are disclosed.

Abstract: A floor system for a cabin of a vehicle is proposed, the floor system including a floor panel having a bottom layer, a top layer and a continuous stiffening structure having an alternating arrangement of elongated first depressions and elongated protrusions arranged between the bottom layer and the top layer, an elongated cover component, and at least one seat rail component. The cover component has an upper surface, a lower surface, and an elongated second depression reaching from the upper surface to the lower surface and having a shape that corresponds to the shape of the first depressions. The cover component is configured to be mounted inside a first depression that is accessible through an elongated cutout extending along a depression of the stiffening structure. The at least one seat rail component is attachable to the cover component to provide a seat rail along the floor panel.

Abstract: An aircraft with an aircraft fuselage, and a passenger cabin and a cockpit, where the aircraft includes a center-forward attendant space between the passenger cabin and the cockpit. A cabin crew member of the aircraft can stand in the center-forward attendant space for monitoring progress of an emergency evacuation of the aircraft. The aircraft has one or more emergency exits for providing egress of passengers from the aircraft fuselage during the emergency evacuation. The aircraft also has a situational awareness monitoring (SAM) system for use in evacuating the passengers from the aircraft during the emergency evacuation. The SAM system includes one or more imaging devices and one or more display modules, each of which displays within the passenger cabin images captured by a corresponding one of the one or more imaging devices.