Abstract: A storage compartment arrangement for a vehicle cabin having a storage compartment, housing, closable storage compartment opening, lower compartment section in the housing, and upper compartment section in the housing. The storage compartment opening extends over the structural heights of both compartment sections. Items of luggage can be placed onto a lower horizontal pivoting edge and pushed into the lower compartment section. An upper horizontal pivoting edge is provided onto which items of luggage can be placed and can be pushed into the upper compartment section. The storage compartment opening has an upper opening edge facing an upper side of the upper compartment section and is adjoined by an auxiliary surface extending over the upper compartment section, is at an angle in a range of 10° to 50° to the separating plane, and, as the distance from the upper delimitation increases, encloses an increasing distance from the separating plane.

Abstract: An assembly including a link axis supported by first and second guiding rings positioned in first and second branches of a clevis, one of the guiding rings including a tubular extension, protruding with respect to an outer face of one of the branches, which has a threaded portion on its outer circumferential face. Complementing this, the assembly includes a nut configured to be screwed onto the threaded portion of the tubular extension and an immobilization system configured to immobilize the nut in translation and/or in rotation, the nut and the link axis being linked by a complete link that is non-removable or that forms a single-piece part. This solution makes it possible to reduce the number of parts forming the assembly. Also provided are an engine attachment and an aircraft including such an assembly.

Abstract: A wing for an aircraft, including a main wing, and a leading edge high lift assembly including a high lift body, and a connection assembly connecting the high lift body to the main wing such that the high lift body is movable relative to the main wing between a stowed position and a deployed position. The connection assembly includes at least one rotation element mounted to the high lift body and mounted to the main wing rotatably about an axis of rotation. The high lift body includes a rigid portion and a flexible skin portion. The rigid portion is mounted to the rotation element. The flexible skin portion is connected to a leading edge portion of an upper skin panel of the main wing and is connected to the rigid portion of the high lift body The flexible skin portion is configured to be deformed between a stowed deformation state and a deployed deformation state, when the high lift body is moved between the stowed position and the deployed position.

Abstract: To reduce vibration of movable airfoil structures, such as rudders, elevators, and ailerons, a spring device, a leaf spring for example, is mounted to an airfoil mounting structure, such as a vertical tail plane, horizontal tail plane or the wings, such that the spring device exerts a force on a cam device, which transforms the spring force into an airfoil torque. The airfoil torque is applied to the airfoil structure and thus reduces a risk of vibration. The cam device is configured to redirect the spring force such that when the airfoil structure is moved in a first direction, torque decreases and when moved in the opposite second direction the torque is zero.

Abstract: An elongate antenna assembly (1) for an aircraft including a structural section (3) and an antenna element (5), wherein the structural section (3) includes an elongate leading edge section (7) extending in a longitudinal direction (13) of the antenna assembly, a first lateral section (9), and a second lateral section (11), wherein the leading edge section (7) is curved such that the leading edge section (7) comprises a convex outer surface (15) extending in the longitudinal direction (13) of the antenna assembly (1) on a convex side (19) of the antenna assembly.

Abstract: A leading-edge arrangement for an aircraft is proposed, comprising a plurality of movable flow bodies, a supply duct, an air transfer duct, and at least one perforated tube. The movable flow bodies are arranged in a consecutive arrangement to form a row with a first end and a second end. The supply duct reaches into an interior of one of the flow bodies at the first end. The air transfer duct connects to the supply duct and extends at least through the interior of the respective flow body in the direction towards the second end. The at least one perforated tube is arranged inside at least one of the flow bodies that directly follows on. The at least one perforated tube is in fluid communication with the transfer duct. The transfer duct is configured to transfer air from the supply duct into the at least one perforated tube.

Abstract: A system for controlling idle speed and power draw includes a determination unit configured to determine a current available power value, a determination unit configured to determine a current power consumption value, a determination unit configured to determine a future power requirement variation value, a computation unit configured to calculate a future estimated total power requirement value, a computation unit configured to calculate a future estimated available power value, an optimization unit configured to determine an optimization result by comparing the estimated total power requirement value with a power value associated with an optimization criterion and a controller configured to send an order to adapt an idle speed of the engine, an order to adapt the estimated total power requirement or no order as a function of the optimization result.

Abstract: An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a front portion blended into and extending rearwardly from the leading edge of the fixed wing and the wing tip device.

Abstract: A method of communicating configuration data of a tire pressure monitoring device configured to be affixed to a wheel is disclosed. The method includes, at the tire pressure monitoring device, receiving a request to confirm configuration data, and responsive to receipt of the request to confirm configuration data, transmitting a configuration data signal which encodes the configuration data. The configuration data signal is configured to be received and understood by a human.

Abstract: Leakage detection for pressurized fuel tanks. To provide facilitated leakage detection, a leakage detection device for pressurized fuel tanks for storing a pressurized fuel includes a fuel-sensing tracer and a light-wave conducting component. The fuel sensing tracer is configured to alter its optical properties in the presence of a predetermined fuel. The light-wave conducting component is in optical contact with the fuel sensing tracer. Light travelling within the light-wave conducting component is modifiable by altered optical properties of the fuel sensing tracer such that modified light is indicative of the presence of fuel at the location of the fuel sensing tracer.

Abstract: An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.

Abstract: An aircraft wingbox assembly is disclosed having a wingbox with an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox. The ribs divide the wingbox into bays. A fuel tank is in a first one of the bays. One of the spars includes a spar hole which is configured to enable the fuel tank to be removed from the first one of the bays through the spar hole.

Abstract: Method and device for manufacturing a component from a plate made of deformable material, in particular for an edge of an element of an aircraft. The device includes a tool with two tool parts configured to be able to move closer to one another and are able to round a plate made of deformable material fixed to the two tool parts, a mold at the periphery of the tool and including a molding cavity of a shape corresponding to the shape of the component that is to be manufactured, and a displacement system configured to press the rounded plate firmly against the molding cavity of the mold, the mold being able to shape the rounded plate when it is pressed firmly against the molding cavity to give it its definitive shape, the device allowing the manufacture of single-piece components of varying sizes and notably large-sized components and/or deep components.

Abstract: A simple and lightweight system for discharging water that can flow out through an orifice in an insulation blanket lining the walls of a fuselage of a transport vehicle such as an aircraft. The blanket has an impermeable collection plate having at least partially the shape of a channel, container or the like for collecting and discharging condensation water under the effect of gravity through an orifice.

Abstract: A fastening apparatus and fastening arrangement for fastening a cabin interior component, aircraft cabin and aircraft. To improve installation time and maintenance time, a modular fastening apparatus makes the decoupled rotational attachment of cabin interior components to the attachment structure possible, which attachment structure is in turn supported by the primary structure of the aircraft. The cabin interior component, for example a luggage bin, can be fastened simply by the fastening apparatus. The fastening apparatus includes an inner sleeve which can be plugged over a predefined fastening tube. The fastening apparatus can compensate for tolerances between the attachment structure and the cabin interior component and can prevent transmission of undesired forces and torques.

Abstract: A fastening system for an aircraft configured to fasten at least one tank intended to contain liquid hydrogen includes a longitudinal box, an upper structure fastened to an upper side of the longitudinal box, a lower structure fastened to a lower side of the longitudinal box and at least two fastening frames including, on either side of the vertical plane of symmetry (P1), a fastening device for connecting a tank to the upper structure. The fastening system further includes at least two fastening devices for connecting a fastening point of the tank to the longitudinal box and at least two fastening devices for connecting a fastening point of the tank to the lower structure. The fastening system makes it possible to securely fasten at least one hydrogen tank on board an aircraft (AC).

Abstract: A single acting actuator for an aircraft landing gear assembly is disclosed having a piston mounted in a cavity and moveable relative to a housing between a retracted position and an extended position, the piston dividing the cavity into first and second pressure chambers. At least one of the pressure chambers is associated with first and second outlets, with the actuator being arranged such that, in respect of the relative movement in which the pressure chamber is the decreasing volume pressure chamber, in a first stage of the relative movement the first and second outlets are open thereby allowing actuator fluid to flow out of the pressure chamber through the first and second outlets and in a second stage of the relative movement the second outlet is open but the first outlet is closed, thereby acting to slow the relative movement of the piston with respect to the housing.

Abstract: A wing for an aircraft is disclosed including a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.

Abstract: A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the hinge axis. The wing includes a brake unit for securing the foldable wing tip portion in the folded position, and the brake unit is formed separately from the actuation unit.

Abstract: A fluid transport device includes a conduit unit having a wall for separating an inside from an outside of the conduit unit. The device also includes an energy supply unit coupled to the conduit unit and configured to provide electrical energy based on a temperature gradient between the inside and the outside of the conduit unit. The device also includes a monitoring unit configured to monitor a state of the conduit unit and to generate data representative for the state of the conduit unit. The energy supply unit supplies the electrical energy to the monitoring unit, thereby enabling the monitoring unit to monitor the state of the conduit unit. A method for manufacturing a fluid transport device is also described.