Abstract: A method for producing a component from a fiber-reinforced plastic, wherein at least one ply of a semifinished fiber product having a peripheral contour is applied to the molding tool at a first temperature, wherein the contour lies within the peripheral edge. A compensating body, having a coefficient of thermal expansion which is greater than a coefficient of thermal expansion of the molding tool, is arranged along the peripheral edge, such that the compensating body extends from the edge in the direction of the peripheral contour. After sealing the arrangement, resin is introduced, and the arrangement is heated. As a result, the compensating body expands to a greater extent than the molding tool and encloses the semifinished fiber product in a flush manner, with the result that a shape of the component can correspond to an intended final shape and no longer has to be finish-machined.

Abstract: A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Abstract: An aircraft wing including: a main wing portion with a tip end, and a wing tip device rotatably coupled to the tip end of the main wing portion at a joint, the wing tip device rotatable at the joint about a first axis between a flight configuration and a ground configuration; and a seal panel assembly including: a seal panel extending across the joint; a first connecting element having a first end non-rotatably coupled to the seal panel and a second end rotatably coupled to the main wing portion such that the seal panel is rotatable about a second axis; and a second connecting element having a first end rotatably coupled to the seal panel and a second end rotatably coupled to the wing tip device, such that rotation of the wing tip device about the first axis causes the seal panel to rotate about the second axis.

Abstract: A pipe connecting system for first and second pipe pieces extending along a common longitudinal axis includes a clamp. The pipe pieces each have first end and first clamping surfaces. The clamp has first and second contact surfaces lying against respective clamping surfaces to prevent the clamping surfaces from moving away from one another, while leaving a space between the first and second end surfaces. A retaining ring has a sealing connection attachment to the second pipe piece, and on which a sealing ring is mounted, the sealing ring lying against a circumferential first sealing surface of the first pipe piece. An interior of the first and second pipe pieces between the two pipe pieces is sealed against the surrounding environment by the sealing connection. The two pipe pieces can move towards one another without the first sealing ring moving out of contact with the first sealing surface.

Abstract: A method for processing previously detected identifications of apparatuses of an aircraft, wherein each apparatus has at least one communicative component. A reference dataset is used to compare the actual identifications with specified identifications, as a result of which a report signal based on the comparison result indicates whether the detected identifications correspond to the identifications represented by the reference dataset. If there is a positive match, this allows the conclusion that the apparatuses are correctly installed in the aircraft.

Abstract: An aircraft braking system for an aircraft, the aircraft including first and second brakes, and first and second energy distribution systems for delivering energy to the first and second brakes to operate the respective first and second brakes. The aircraft braking system is switchable between: a first configuration, in which the first energy distribution system is coupled to the first brake and is isolated from the second brake, and the second energy distribution system is coupled to the second brake and is isolated from the first brake; and a second configuration, in which the first energy distribution system is coupled to both the first and second brakes.

Abstract: An aircraft system for an aircraft is disclosed having a controller that is configured, during a take-off procedure, to initiate, prior to receiving a command to retract a landing gear, automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position, on the basis of a determination, made when a speed of the aircraft is determined by the controller to be equal to or greater than a first threshold speed, that a one engine inoperative condition is met.

Abstract: A structure for an aircraft is disclosed including comprising at least one node which having first and second plates which are pressed against two opposite faces of a first reinforcement, and to which upstream and downstream reinforcements positioned on either side of the first reinforcement are connected. A connection system connecting the first and second plates is disclosed including at least one boss projecting from a surface of one of the plates pressed against the first reinforcement, for each boss, a housing recessed relative to a surface of the other plate pressed against the first reinforcement, configured to house the boss, and at least one fastening element, passing through the first reinforcement, connecting the first and second plates and spaced apart from the boss.

Abstract: A system and method for welding two thermoplastic workpieces. The system has an ultrasonic tool, a support and a cooling unit. The ultrasonic tool is configured to generate mechanical vibrations. The system is configured to clamp together workpieces in the receiving region by the ultrasonic tool and the support if at least one fastening portion of the workpieces opposite one another is arranged in the receiving region. The ultrasonic tool is configured to introduce the mechanical vibrations into the fastening portion of the workpieces to weld the workpieces in a joining zone. The cooling unit is configured to cool, with cooling fluid, at least a part of the fastening portion of the workpieces and/or a cooling portion of the workpieces directly adjacent to the fastening portion.

Abstract: A shock absorber for an aircraft landing gear is disclosed. The shock absorber includes a stop surface arranged to limit extension of the shock absorber and a crumple element configured to deform in the event that the extension load on the stop surface exceeds a predetermined threshold. The crumple element may form part of the out-stop tube of the shock absorber. Deformation of the crumple element may be identified by measuring the length of the fully extending landing gear, through non-destructive testing or by measuring the change in conductance of the crumple element.

Abstract: A flow control device on a structure such that strain in the structure is at least partially transferred to the flow control device is disclosed having at least two states, or shapes, separated by an elastic instability region. The flow control device is arranged to rapidly transition, or snap through, from the first state to the second state when strain in the structure exceeds an activation threshold of the flow control device. A spoiler on an aerofoil has a rest position where it is substantially flush with the low pressure surface and an activated position where it protrudes from the low pressure surface and modifies the airflow over that surface. The spoiler bends to move from the rest position to the activated position when the strain in the aerofoil crosses a threshold. The deployed spoiler reduces the lift on the aerofoil, acting to reduce the lift induced strain of the aerofoil to which the spoiler is attached.

Abstract: A kit of parts for forming an aerofoil assembly is disclosed having a torsion box structure including a first attachment point and a second attachment point, the first and second attachment points being separated from each other along a separation axis, and a fixed leading or trailing edge structure including corresponding first and second attachment points, wherein a first structure includes a slidebly mounted abutment piece slideable along a slide path extending in a direction parallel to the separation axis and a fixing mechanism for fixing the slidebly mounted abutment piece. A second structure includes a corresponding abutment feature having a first abutment surface facing in a direction parallel to the separation axis of the second structure, such that, in use, the abutment piece prevents relative movement of the first and second structures.

Abstract: A brake control system 200 and method 300 for controlling a park brake of an aircraft including a controller 201 configured to cause an increase in a brake torque of the park brake based of an indication to the controller. The indication is generated in response to touchdown of the aircraft.

Abstract: A command system of an aircraft mobile element actuated by a motor is provided. The command system is electrically connected to a power supply, to the motor and to a current consuming device used to effect de-icing. The system establishes a connection between the motor and the current consuming device and inhibits a first connection between the power supply and the motor and a second connection between the power supply and the current consuming device when a braking command is received. The system enables the first connection and the second connection to be established and inhibits the third connection as long as no braking command has been received or when a command to stop braking is received. Thus the mobile element can be easily braked and the overall size of the system is limited.

Abstract: A tank configured to store a liquid and that includes at least one capture device which includes at least a first portion of a line situated at the bottom of the tank, close to its first end, and at least a second portion of the line situated at the bottom of the tank, close to its second end, each of the first and second portions including at least one orifice situated on the upper face thereof, a floating shut-off device for each orifice, the floating shut-off device being movable between an open position in which the floating shut-off device is spaced apart from the orifice and a closed position in which the floating shut-off device shuts off the orifice, the floating shut-off device having a density lower than that of the liquid stored in the tank.

Abstract: A method of copying data from a first device to a second device, each device including a wireless communication interfaces having a maximum range, is disclosed. The first device and the second device are separated by a distance greater than the maximum range. The method includes: transmitting, by the first device, the data to a third device positioned within the maximum range of the first device; receiving the data at the third device and storing the data in a memory of the third device; moving the third device to a physical location within the maximum range of the second device; and transmitting, by the third device, the data to the second device.

Abstract: A flow body for an aircraft is disclosed having a stiffening structure and a flow surface at least partially enclosing the stiffening structure, the flow surface having a leading edge and a trailing edge at a distance to each other in a chordwise direction, the flow body including a first heating device attached to or integrated into the flow surface in a first chordwise section, a second heating device attached to or integrated into the surface body in a second chordwise section. The first chordwise section and the second chordwise section are distanced from each other, the first chordwise section is closer to the leading edge than the second chordwise section, and at least the second heating device comprises an electric heater.

Abstract: An auxiliary power unit system of an aircraft includes an auxiliary power unit (APU), a cooling unit for the APU including a heat exchanger, an air inlet in communication with the APU and/or with the cooling unit, an air inlet door unit located at the air inlet, a first duct configured to draw air into the APU and having an entrance in communication with the air inlet, a second duct having an entrance in communication with the air inlet, the heat exchanger being at least partially located within the second duct, an air turbine located within the second duct downstream of the heat exchanger, and an electrical generator coupled to the air turbine.

Abstract: A structural element for a passenger cabin of an aircraft is built using biomimicry methods. The structural element includes a generative structure, and a functional component. The generative structure includes at least one accommodating space. The functional component is arranged within the at least one accommodating space. The generative structure includes a load topology optimized structure based on a bioinspired generative design that is configured to enable the structural integrity of the structural element while simultaneously providing integrated functionalities via the functional component. Further, an interior component for an aircraft is disclosed that includes at least one such structural element, and an aircraft including at least one structural element. For example, an aircraft galley may include a structural component that may therefore, for example, include integrated wiring, plumbing or other functionalities.

Abstract: A computer-implemented method of aircraft tire maintenance is disclosed including the steps of receiving data of a plurality of pressure and temperature measurements, each of the plurality of pressure and temperature measurements having an associated time stamp; determining stable points in the plurality of pressure and temperature measurements; and using the stable points for determining tire maintenance. A computer readable medium with instructions to implement the method and a processing system to implement the method are also disclosed.