Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

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 inflatable separating region for a vehicle interior, in particular for a passenger cabin of an aircraft, includes a supporting structure with interconnected inflatable tubes made of a flexible material and arranged, in an inflated state, to form a self-supporting frame structure for the separating region; and a covering with flexible wall membranes which connect the inflatable tubes to one another in a planar manner to separate off the separating region in the inflated state from the vehicle interior.

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: An active trim system of a flight control system of an aircraft that transmits a tactile feel to a pilot of the aircraft in response to a manoeuvre. The active trim system includes: a manual control member (6) an elastic deformation means (1) and a reversible actuator (2), intermediate linkage member (4) and a controller. The actuator (2) includes a rod (5) and a motor (3) parallel to the elastic deformation means (1) and is movable by the motor (3) and by the motion of the manual control member (6). The intermediate linkage member (4) is linked to the manual control member (6) between the manual control member (6) and the elastic deformation means (1) and the reversible actuator (2), a controller configured to: move the reversible actuator (2) to a predetermined zero position, and to provide stiffness against a displacement of the intermediate linkage member (4).

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 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 rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.

Abstract: A retractable landing gear for an aircraft. The landing gear comprises a rocker arm hinged to a structure of the aircraft and carrying at least one wheel that is able to move between a deployed position and a retracted position, a shock-absorber hinged to the structure, a connecting rod connecting the rocker arm and the shock-absorber, a strut provided with two connecting links that are hinged to each other and respectively hinged to shock-absorber and connected to an actuator fastened to the structure. The connecting rod is out of alignment with the shock-absorber when a force applied to the shock-absorber is less than a predetermined force, and the landing gear comprises a locking device provided with an elastic return member and a stop device for locking the strut when the wheel is in the deployed position, and then for securing the wheel in the deployed position.

Abstract: A rotorcraft provided with a rotary wing and a skid landing gear, the landing gear being provided with a first skid and a second skid and with a first cross-member and a second cross-member. The first cross-member is connected to an airframe of the rotorcraft only by two fastenings. The second cross-member is only carried during flight by two supports fastened to the airframe and traversed by the second cross-member. Each support comprises a hole delimited by a stop surface, the second cross-member always being separated from each stop surface by a clearance. A median supporting member is arranged transversely between the two supports and above the second cross-member.

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 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 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 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 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 electrical-energy transfer device comprising first and second parts able to move one relative to the other between distanced and close-up states, the first part comprising a first housing configured to at least partially house the second part, comprising at least a first lateral surface on which at least a first electrical-energy transfer element is positioned, the second part having a second lateral surface for each first lateral surface of the housing, having an overall shape that complements the shape of the first housing and on which surface there is positioned at least one second electrical-energy transfer element, the first and second electrical-energy transfer elements performing a transfer of electrical energy between one another when the first and second parts are in the close-up state.

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.

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.