Abstract: A fuel tank installation comprising: a fuel tank for holding fuel, the fuel tank comprising a fuel tank wall formed with a hole; a fuel pump assembly fitted into the hole in the fuel tank wall with an inner part of the fuel pump assembly protruding from an inner side of the hole and an outer part of the fuel pump assembly protruding from an outer side of the hole; a cage surrounding the outer part of the fuel pump assembly; and a mounting piece which attaches both the cage and the fuel pump assembly to the fuel tank wall.

Abstract: A standardized wall mounting is provided for mounting control units of system components in an aircraft cabin with a fastening unit and at least one plug unit. The fastening unit is designed for guiding the control unit during an installation movement of the control unit on the wall mounting. The plug unit is designed for producing a plug connection between the control unit and the wall mounting during the installation movement of the control unit on the wall mounting.

Abstract: The invention relates to a device for welding a stiffener to a skin. The stiffener has a stiffener foot with a bearing surface parallel to the skin surface and a stiffener flange projecting away from the plane of the bearing surface. The device includes a metallic support includes a seating surface matching the shape of the receiving side; a groove which accommodates a flange of the stiffener inserted in the groove; an insulative supporting structure for positioning a bearing surface against the receiving side; and a conformal panel for applying pressure forcing said bearing surface against said receiving side. A heater temporarily raises the temperature of bearing surface of the stiffener and the adjacent receiving side of the skin to above the melting point of the matrix when pressure is applied thereby welding the stiffener to the skin.

Abstract: A method and device for measuring the flow speed of a fluid, in one example, of air, is provided.

Abstract: A water system for a vehicle is provided. The water system comprises at least one water supply source, at least one water-conducting device, at least one closing valve and at least one germ reduction connection. The germ reduction connection and the water supply source are connected to the water-conducting device. The germ reduction connection is designed to introduce a germ-reducing fluid into the water-conducting device. The closing valve is arranged between the water supply source and the germ reduction connection and is designed to be fully closed thus preventing the ingress of germ-reducing fluid into the water supply source. By means of such a water system it is possible to carry out sterilization or disinfection very easily and quickly without this requiring any major maintenance work.

Abstract: A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap support beam including an aerodynamic fairing; and a drive unit including a universal support structure which rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing.

Abstract: A joining apparatus for joining together structural components of an aircraft, includes positioning means for holding the structural components to be joined in a defined desired position, in which the structural components can be fixedly joined together by means of a joining device that can be moved relative to the structural components by way of guiding means, wherein the positioning means encompass a formative frame structure that is detachably secured to the structural components to be connected along the joining edges outside in the edge area, and serves as a guiding means for the joining device movably secured hereupon.

Abstract: An actuation device for opening an emergency exit flap of a cockpit door is provided. The actuation device comprises a support structure, at least two securing elements, an actuation element and a deflection mechanism. The support structure is configured so as to be fastened to the emergency exit flap. The securing elements are integrated into the support structure and are configured so as to fasten the actuation device, and thus the emergency exit flap, to the cockpit door. The actuation element is connected to the support structure. Therein, the deflection mechanism connects the securing elements to the actuation element in such a way that a force which is exerted on the actuation element is diverted in such a way that the securing elements are released from the cockpit door.

Abstract: A method is provided for destroying a blind fastener joining at least two parts. The blind fastener includes, but is not limited to a body situated in the holes provided in the joined parts, with a head at each end thereof, and portions of which protrude above the level of the holes. The method also includes, but is not limited to withdrawing the accessible head of the fastener, and creating a hole that passes through the fastener. An insertion device is configured to restrain the remainder of the fastener in the hole, which has an elongated body having a diameter smaller than or equal to that of the hole and an expandable head at one end thereof The insertion device for restraining the remainder of the fastener being immobilised or capable of only limited movement relative to the joined parts, and expelling the remainder of the fastener from the holes.

Abstract: An APU air intake (AI) is disclosed having a foldable intake door (101), comprising a frame (102) with airfoil profiles (103, 103a, 103b). The frame (102) is turned to an aperture angle (?) with respect to the frame support (121), and each airfoil profile (103, 103a, 103b) is turned to a profile angle (?i) with respect to the frame (102). The aperture angle (?) varies from 0° to 22°, and the profile angles (?i) vary from 0° to 110°. The frame (102) is moved by an actuator (109) and the airfoil profiles (103a, 103b) are operated by extendable rods (111) and secondary rods (118), each secondary rod (118) having rod supports (119a, 119b). A latching mechanism is assembled onto each extendable rod (111), comprising a rare earth magnet (112) and either a magnet contact plate (113) or a plate with another magnet.

Abstract: A module in the form of a pallet or a closed container includes a grouping together of the electrical devices in an avionics bay, in which the electrical devices are interconnected and attached so as to facilitate the mounting and thus limit the time it takes to mount the electrical devices in the avionics bay.

Abstract: A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means.

Abstract: A computer-implemented method for converting a representation of a system into a behaviour model of the system is provided. The method can be used to convert a schematic diagram into a behavioural model.

Abstract: The invention pertains to a protective device for a pressure line for conveying pressurized fluids, as well as to a pressure line section with a pressure line for conveying pressurized fluids and a corresponding protective device.

Abstract: A computer-implemented method for determining a configuration of a plurality of components in a systems installation which satisfies one or more constraints.

Abstract: A system for air conditioning an aircraft cabin is provided. The system includes at least one cooling circuit, at least one compressed-air line and at least one compressor for compressing air. The cooling circuit is connected to the compressor by way of the compressed-air line, and the compressor is drivable independently of bleed air. This makes it possible to tap engine bleed air at a lower pressure than usual, because an arising difference from a required operating pressure can be compensated for by the compressor. The air conditioning system can thus be operated by means of a hybrid energy supply.

Abstract: A handling system for handling objects in a vehicle comprises a storage apparatus that is positionable outside a vehicle cabin, an access device that is positionable in a vehicle cabin, and a transport device for transporting objects between the storage apparatus and the access device. The storage apparatus comprises a storage space and a connection station that is connectable to the transport device, wherein the storage apparatus comprises at least one drive device for moving carriers on which objects to be stored are held. The handling system comprises at least one guiding device that with the drive device guides the carriers on at least one circular path within the storage space. The storage space thus comprises a vertical flat shape that results in a significantly smaller reduction in the available cargo volume in a vehicle, while at the same time maximizing the design space available for passenger seats.

Abstract: The invention comprises, a first preliminary step of cleaning the treatment surface of the moulding base tool and a second step in which the necessary layers of mould-release agent are applied to the treatment surface of the moulding base tool. Based on said preliminary steps, the process is characterized in that, in a later step, the treatment surface (1), covered with a mould-release agent (3), is provided with a continuous uniform film (4) of resin having a low concentration of volatile elements and a laminar resin supporting a very high mould-release capability, which facilitates the transfer of resin to the treatment surface (1) of the moulding base tool (2).

Abstract: The invention relates to a wing with an extension in the wingspan direction, in the wing chord direction and in the wing thickness direction for use in an aircraft, with a retractable wing end piece. A mechanical lever system is here used, which can execute a pivoting motion of a wing end piece comprising both a rotational component and a translational component. The lever kinematics here comprises two lever arrangements, for which a respective two hinged devices are provided.

Abstract: An apparatus for measuring an air pressure includes a linear retaining means, a towed device, at least one pressure sensor for acquiring a static pressure, and an actuating device that can be positioned in an aircraft, for retracting and extending the linear retaining means. The towed device includes an enclosure, an autarchic voltage supply and a wireless first communication device that is connected to the autarchic voltage supply. The first communication device is equipped to transmit signals and/or data that represent acquired measurement data to a second communication device. Consequently, the linear retaining means can be attuned purely to the task of retaining the towed device and does not need to carry out any secondary tasks of transmitting signals and/or measured data.