Abstract: A fluid pipe connection is disclosed having an inner pipe assembly including a first inner pipe section and a second inner pipe section, and an inner joint between the first inner pipe section and second inner pipe section; an outer pipe assembly having a first outer pipe section, a second outer pipe section, a shroud covering the inner joint and mechanically connecting the first outer pipe section to the second outer pipe section via a mechanical connection, and a hatch fastened to the shroud by one or more fasteners and covering a hole in the shroud, wherein the hatch is moveable between a closed position and an open position to provide access to the inner joint through the hole.

Abstract: A valve for a hydraulic circuit for an aircraft, the valve being configured to unite or separate multiple circuit portions in at least two configurations. More particularly, the valve allows to create one hydraulic circuit or two independent hydraulic circuits in order to circulate a coolant in two distinct manners and thus to adapt the function of the hydraulic circuit to any of two distinct phases of the functioning of an engine of the aircraft.

Abstract: An actuator assembly for moving a movable aerodynamic surface of an aircraft is disclosed including an input section for introducing an externally provided rotary motion into the actuator assembly, and a geared rotary actuator having at least one actuator slice having a planetary gear with a sun gear couplable to the input section, a fixed gear attachable to a fixed component of the aircraft and an output gear couplable with the movable aerodynamic surface. At least one clutch is connected to the geared rotary actuator and is configured to couple the movable surface with the input section and to selectively decouple the movable surface from the input section, such that it is freely movable.

Abstract: A fastening system includes a first fastening element attachable to a structure and which has a base portion for plugging through a structural opening, a second fastening element, and a plastically deformable funnel element. The funnel element has a funnel-like basic shape with a funnel opening. The second fastening element can be introduced through the funnel opening into a receiving opening of the base portion and fastened therein and has a collar which faces away from the receiving opening and which is larger than the funnel opening. The funnel element is designed to be deformed from the funnel-like basic shape into a flat, disk-like final shape by the collar of the second fastening element during the fastening of the second fastening element.

Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

Abstract: A method for combined cooling and heating in an aircraft, the aircraft including an engine configured to use dihydrogen as fuel, the dihydrogen being stored in liquid form in a tank and being used in gas form in the engine, the dihydrogen being conveyed from the tank to the engine by a main pipe. The method includes the steps of branching off a part of the flow of dihydrogen in a bypass pipe, in parallel with a predefined segment of the main pipe, circulating a first heat transfer fluid in a first closed circuit, carrying out a first heat exchange between the first heat transfer fluid and the dihydrogen circulating in the bypass pipe and carrying out at least one secondary heat exchange. Each secondary heat exchange is carried out between the first heat transfer fluid and a working fluid used in the aircraft which needs to be cooled.

Abstract: Film for the repair of aircraft components made of fiber-reinforced thermoplastic including an embossed film made of polyimide and a coating made of an electrically conductive material.

Abstract: A cryogenic fluid pressure vessel for an aircraft, having: a first wall layer, which contains carbon fiber-reinforced plastic, having an inner contact surface for the contact with a pressurized cryogenic fluid to be accommodated inside the cryogenic fluid pressure vessel; a second wall layer, which is arranged on an outer surface of the first wall layer and has a thermal barrier; a closable inlet/outlet opening for cryogenic fluid, which extends through the first and the second wall layer; and a structural insert integrated in the first and the second wall layer, which has a fastening connecting piece located on the outside of the cryogenic fluid pressure vessel for mechanically coupling the cryogenic fluid pressure vessel with external structures; wherein the cryogenic fluid pressure vessel forms an essentially cylindrical main body. Furthermore, the present invention provides an aircraft having such a cryogenic fluid pressure vessel.

Abstract: A leading edge assembly for an aircraft wing. The leading edge assembly includes a housing configured to be connectable to a fixed wing section of the wing, the housing formed with a first opening connecting an exterior of the housing with an interior of the housing, an actuating element movably connected to the housing, such that the actuating element is movable between a first position and at least one second position. The actuating element extends through the first opening and includes a first section arranged in the interior of the housing and a second section arranged at the exterior of the housing. The actuating element is configured to be connectable to a high lift device.

Abstract: A method for producing a component with a surface that is suitable for plastic welding or adhesive bonding of two parts is provided. As a preparation step prior to joining, a filler sheet comprising a thermoplastic material or adhesive is arranged on a first surface of a first component and a structuring tool is arranged on the filler sheet. Mechanical force is applied to the structuring tool and heat is applied to the filler sheet such that the filler sheet is attached to the first surface of the first component and such that the structuring tool is partially embedded in the filler sheet. The structuring tool is subsequently removed from the filler sheet to produce a plurality of protrusions in the outer surface of the filler sheet. After surface structuring the first and second components are joined using any type of welding technique or joined using of adhesive bonding.

Abstract: A system for positioning vehicle components relative to each other on a floor to prepare an assembly. A plurality of carriers receive a vehicle component. A plurality of positioning tables have a lower portions which can be fixed to the floor and a upper portions which receive a carrier. A location device having at least one base and mobile units moveable relative to the base. At some of the positioning tables moves the respective upper portion along at least two movement axes relative to the respective lower portion to position a carrier located thereon. A transport device guides the carriers from an external position to a positioning table and to place them on the upper portion. The location device determines the positions of the respective mobile units relative to the at least one base. A position control unit controls a movement of the upper portions to a predetermined target position.

Abstract: A device (1) including an ultrasonic measuring unit (7) that sends an ultrasonic signal (S1) into a structure (2) and measures the amplitude of the ultrasonic signal (S2) reflected by the structure (2), a processing unit for determining the thickness of the interposition mastic (3) from the measurements of the ultrasonic measuring unit (7) and with the aid of a propagation model of the interposition mastic (3) which provides a thickness value of the interposition mastic (3) depending on the propagation time of the ultrasonic signal in the interposition mastic (3) as well as auxiliary data, and a processing unit for deducing a conformity or a lack of conformity of said interposition mastic (3) and the presence of cuttings from the thickness of the interposition mastic (3), the device (1) carrying out a conformity checking that is accurate, fast and reliable without having to disassemble the structure (2).

Abstract: A method for the selective modification of position information for a throttle lever. The method is implemented by a device configured to receive position information representing a current position of the throttle lever. The method includes determining that a predefined situation is encountered when a flight condition associated with the predefined situation is verified, and obtaining, for each encountered predefined situation, a category, a duration and an expected position of the throttle lever. The method includes modifying the received position information by replacing it with the expected position, when the flight condition and a validity condition of the category are simultaneously verified for said obtained duration, and sending the modified position information in the event of a modification to a control device of the propulsion engine. Thus, it is possible to automatically influence the thrust of the engine when required by the situation.

Abstract: An aircraft system (10) for an aircraft (1) including a controller (100) configured to receive at least one signal during a take-off procedure of the aircraft. The signal includes information representative of at least one parameter of the aircraft. The controller is configured to determine whether a current or future aircraft climb rate associated with the take-off procedure meets a criterion, on the basis of the at least one signal. The controller is configured to determine at least one remedial action to be taken, such as performance of at least a portion of a procedure to retract a landing gear of the aircraft, when the controller determines that the aircraft climb rate does not meet the criterion.

Abstract: A lavatory door system for a vehicle, in particular an aircraft, with a lavatory door; a pneumatic actuator configured to open and close the lavatory door based on a differential pressure, wherein the pneumatic actuator is coupled to a vacuum toilet system of the vehicle to generate the differential pressure; and an operating interface configured to receive a user control operation and to selectively release the differential pressure from the vacuum toilet system for operation of the pneumatic actuator based on the received user control operation.

Abstract: A computer-implemented method of obtaining an excursion report for an aircraft is disclosed. The aircraft includes one or more sensors and a vision system, and the method includes obtaining sensor data from the one or more sensors; storing and time-stamping the sensor data; operating the vision system to detect the aircraft leaving a runway or taxiway; recording a start time of an excursion period based on a time of detection of the aircraft leaving the runway or taxiway; operating the vision system to detect the aircraft returning to the runway or taxiway; recording an end time of the excursion period based on a time of detection of the aircraft returning to the runway or taxiway; and compiling an excursion report, the excursion report comprising: the start time of the excursion period, the end time of the excursion period and a subset of the sensor data which was time-stamped during the excursion period.

Abstract: An electrical supply system (10) with first and second electrical sourced (S1, S2), coupled together to electrically supply electrical loads (Z1, Z2, Z3 . . . Zn) of an aircraft. The first electrical source (S1) is mechanically coupled to a primary energy source (12), to which at least one other energy consumer (16) is coupled. A controller (30) controls the first and second electrical sources (S1, S2) so that the power drawn by the first electrical source from the primary energy source (12) corresponds to a difference between an instantaneous nominal power capable of being delivered by the primary energy source and an instantaneous power drawn by the energy consumer (16), and an electrical power delivered by the second electrical source is a sum of an electrical power delivered by the first and second electrical sources which corresponds to an instantaneous electrical consumption of the electrical loads.

Abstract: An aircraft wing having a main wing and a trailing edge flight control surface movable between a retracted position, a first extended position in which the control surface is positioned rearwardly in the chord wise direction relative to its retracted position, and a second extended position in which the control surface is rotated relative to its retracted position. A closure panel, mounted to the main wing, extends from the main wing to the control surface, to provide an air flow surface between the main wing and control surface, both when the control surface is in its retracted position and its first extended position. The closure panel is movable, relative to the control surface, to an open configuration in which it opens an airflow passage provided between the control surface and an opposed surface of the aircraft wing when the control surface is in its second extended position.

Abstract: A fastening system for suspended installation of stowage compartments, in particular in aircraft, includes a first fastening element, which fastens on a supporting structure, a second fastening element, which fastens on a stowage compartment, and a connecting arrangement, configured for surface-area fastening on the first fastening element. The connecting arrangement and the second fastening element each include a supporting eyelet for accommodating a fastening bolt, to fasten the connecting arrangement on the second fastening element.

Abstract: An aircraft brake control system for controlling anti-skid braking of at least first and second wheels in a wheel set of an aircraft is disclosed. The system includes a control assembly having wheel speed inputs including an input of an indication of the wheel speed of the first wheel, and an input of an indication of the wheel speed of the second wheel, a wheel speed comparator for determining which of the wheel speeds indicated is a lowest wheel speed, and an output for indicating a wheel speed other than the lowest wheel speed. An aircraft landing gear, an aircraft, and methods of braking an aircraft are also disclosed.