Abstract: A method for a thermal joining of two thermoplastic components includes arranging at least one reactive sheet entity in a mating zone between the two thermoplastic components. A multiply perforated metallic sheet entity configured as a bonding agent is disposed on each side of the at least one reactive sheet entity, at least in some regions of the mating zone. The at least one reactive sheet entity is activated so as thermally join the two thermoplastic components in the regions of the mating zone.

Abstract: A monument is provided for an aircraft. The monument includes, but is not limited to several system components with identical, substantially identical or similar functions that can be connected by way of a single system connection arrangement to the supply in the aircraft. Distribution of the supply media, received by the aircraft, to the individual system components takes place within the monument. The system connections can thus be identical to the system connections of a single monument.

Abstract: An aircraft exterior door installation with a door attached to an airframe. A damper is arranged to damp motion of the door as it is opened by rotating it away from the airframe. A coupling mechanism couples the damper with the door over an opening damping range and decouples the damper from the door at the end of the opening damping range. The damper does not damp the motion of the door as it opens beyond the opening damping range. Instead of damping the door over its full range of motion, it is only damped over a limited inner range of its motion. A further advantage of decoupling the door and the damper is that the damper does not need to extend into the airflow to the same extent as the door, thus minimizing aerodynamic drag.

Abstract: An automatic landing method and device for an aircraft on a runway with strong slope. The device includes means to automatically transmit, a runway slope value to an automatic piloting system of the aircraft, and said automatic piloting system uses the slope value to automatically manage the flare phase upon landing.

Abstract: A process for the production of a part made of composite material including at least one radius of curvature, includes a stage for deposition of pre-impregnated fiber layers (24) on a device (22) of convex shape on one another and for compacting the layers, characterized in that localized and repeated forces are applied in such a way as to cover the zone of the radius of curvature, at a given instant the forces being applied on a zone that is less than half of the zone of the radius of curvature, so as to compact the fiber layers (24) locally during the deposition stage.

Abstract: A cooling system of a vehicle with a fuel cell includes an absorbent circuit with an absorber tank, a regenerator tank, an absorbent pump and a first pressure reduction means and a coolant circuit with a condenser connected to a steam outlet of the regenerator tank, a second pressure reduction means and an evaporator arranged between a steam inlet of the absorber tank and the second pressure reduction means. The regenerator tank is designed to desorb the coolant in solution in the absorbent by absorbing a first quantity of heat and to introduce it in a vaporous state into the condenser. The evaporator is designed to evaporate the coolant while absorbing a second quantity of heat and to introduce it in the vaporous state into the absorber tank. At least one of the first and of the second quantity of heat could be provided by the fuel cell.

Abstract: The present application relates to a shaft locking device. The device has an locking element configured to be mounted on a shaft in a first position so that the locking element indicates the angular position of the shaft. The locking element is also configured to be mounted on a shaft in a second position so that the locking element is locatable against a stop to prevent rotation of the shaft. The present application also relates to a device for determining the angular position of a shaft, a valve assembly and an actuating unit for a valve.

Abstract: A method of testing an electrical junction between a first metallic element and a second metallic element in an aircraft current return network, said network comprising a plurality of metallic elements, each of which is connected to at least two other elements, said aircraft comprising at least one element made of a composite material connected to said network. The method is remarkable in that its use does not damage the composite structure of the aircraft.

Abstract: An aircraft ground or sea approach anomaly detection method. The method includes the steps of characterizing a flight phase of the aircraft, determining a prohibited flight envelope, defining a set of prohibited vertical speeds of the aircraft for given altitudes in relation to the ground or the sea, as a function of the flight phase of the aircraft characterized, and detecting a ground approach anomaly of the aircraft as a function of a current vertical speed and altitude in relation to the ground or the sea of the aircraft, in relation to the prohibited flight envelope determined.

Abstract: An aircraft including a fuselage which extends along a longitudinal axis. The fuselage includes a substantially cylindrical central portion and a rear portion that may have a flattened or conventional shape. This rear portion which comprises the rear end of the fuselage includes a support surface which bears at least one horizontal stabilizer and/or vertical stabilizer. The rear portion is able to pivot in relation to the central portion around an axis such as the pitch axis, at least one stabilizer or the support surface being equipped with at least one control surface.

Abstract: Interactive dialog device between an operator of an aircraft and a guidance system of the aircraft. The dialog device includes an interaction on a screen which represents, on the one hand, a playback element indicating the value of a guidance setpoint of the guidance system of the aircraft, and on the other hand, a control element which can be grasped and moved along a curve by an operator to modify the value of the guidance setpoint.

Abstract: A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face, a sign assembly in the fin body, the assembly comprising a translucent, graphic bearing face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, a recess in the fin body behind the graphic-bearing face, and a light source arranged in the recess to illuminate the graphic-bearing face from inside the fin body.

Abstract: A multifunctional comb includes an upper half-comb provided to be mounted on a support and a lower half-comb provided to be mounted on the support through the upper half-comb and a screw system. The half-combs have arches facing each other to grip the piping. In addition, each of the half-combs has at least two half-bores located in front of each other to form bores of the comb, as well as inter-arches connecting faces. The half-bores, the arches and the connecting faces are continuously covered by an electrically conductive coating in order to ensure the plating function. Moreover, the half-bores, the upper half-comb and the bottom half-comb include structure coupled to the half-combs that can be secured to the support respectively in a temporary and permanent way.

Abstract: An apparatus (10) for fuelling an aircraft, in particular during performing a tank leakage test on the aircraft, comprises a fuel supply line (14) for supplying fuel to an aircraft tank system (12), at least one pressure sensor (26) for sensing a pressure within the aircraft tank system (12) and for providing a signal indicative of the pressure within the aircraft tank system (12), an electronic control unit (ECU) for processing the signal of the pressure sensor (26) and for generating an emergency shut-off signal, if the pressure within the aircraft tank system (12) exceeds a first predetermined level, and an emergency shut-off device (24) which is controlled by the electronic control unit (ECU) and which is adapted to interrupt the supply of fuel to the aircraft tank system (12) in response to the emergency shut-off signal from the electronic control unit (ECU).

Abstract: An earth connection for electrically and mechanically connecting a plurality of earth wires to a structure, in particular to an aircraft structure, comprising an angled element which element is formed in one piece and is made of electrically conductive material, which comprises a first and a second fastening portion. The first fastening portion is fastened to the structure and the second fastening portion comprises a plurality of electrical connections for connecting the earth wires. The electrical connections comprise socket contact elements which are formed so as to receive pin contact elements of the earth wires.

Abstract: A measurement device for measurement of forces in structural components, having a measurement sensor, which is embodied such that it is connected with the structural component in a force-fit and/or form-fit manner, and generates measurement signals as a function of force transfers in the structural component, the measurement device having a measurement casing upon the measurement sensor. Processing of received measurement signals can occur, and the measurement casing has connecting means, for placing in position and releasable attachment of the measurement casing on the structural component, and the contacting means of the measurement casing can establish contact with the measurement sensor for the reception of the measurement signals.

Abstract: A door assembly for a vehicle with two door leaves is stated. In each case the door leaves can be opened in such a manner that the maximum angle of opening between them can be limited. After a door leaf has been opened, the door leaves can thus only be pivoted together so that opening the first door leaf results in closing the second door leaf. As a result of this, access to a space in a vehicle may be controlled.

Abstract: A sealing system (38) for use in an aircraft facility to be sealed from the environment comprises a closing element (40) which can be connected to a housing (42) of the aircraft facility in order to seal an opening (44) formed in the housing (42) of the aircraft facility. Furthermore, the sealing system (38) comprises a receiving device (46), and a sealing element (48) received in the receiving device (46). A transfer device (54) is adapted to transfer the sealing element (48) between an inactive state, in which the sealing element (48) is shaped and/or positioned such that it cannot be brought into sealing contact with a sealing surface (64), and an active state, in which the sealing element (48) is shaped and/or positioned such that it can be brought into sealing contact with the sealing surface (64).

Abstract: A fastening device for attaching a module element to a support structure in an aircraft includes a stud having a first end defining a broadened head configured to engage the support structure, a section which adjoins the head and defines a first lateral dimension and a second lateral dimension that is larger than, and is disposed at least substantially perpendicularly to, the first lateral dimension, and a second opposite end connected to a lever which is movable between open and closed positions relative to the stud. A bushing, which may be electrically conductive, is provided on and longitudinally movable along the stud, which is configured to contact the support structure and to support an outer wall of the module element. An eccentric may be actuated by the lever and is responsive to movement of the lever into the closed position to move the bushing along the stud towards the head.

Abstract: Methods and apparatus for manufacturing a profiled semifinished fiber-reinforced composite (FRC) product from a semifinished product of dry fiber or prepreg material that is moved through a forming device in its longitudinal direction (L), where the semifinished product is moved between the facing forming contours of tool parts in the longitudinal direction of a forming device on a carrier foil and the forming contours of the cross sections of the tool parts continuously change from a cross-sectional contour in the entry region to a forming contour in the outlet region, where a supporting part in the intake region of the forming device is set in vibration in such a way that the semifinished product is transformed into a ductile state due to the frictional heat generated between the supporting part and the semifinished product, and where the speed of the movement of the semifinished product is controlled in dependence on the temperature of the semifinished product.