Abstract: The invention relates to an interconnection, including: a T-stringer which has a web portion and two foot portions; a ?-stringer which has a comb portion and two foot portions; and a connection arrangement which joins together the foot portions of the T-stringer and of the ?-stringer, wherein the connection arrangement joins together the T-stringer and the ?-stringer, wherein the connection arrangement has a first and a second connection element, the connection elements connecting a first foot portion of the T-stringer to a first foot portion of the ?-stringer, respectively, wherein the connection elements together have a substantially H-shaped outline, and wherein at least one angle bracket, in particular for connecting a former to the ?-stringer and the T-stringer, is connected to the widening foot portions of the first and second connection elements.

Abstract: An aircraft nacelle includes a first conduit for an air inlet and a second conduit for an engine, arranged end to end and connected by an annular flange, attached to the air inlet, and an annular flange, attached to the engine. The annular flanges are connected by a plurality of passage holes in the annular flanges and arranged in line with each other. Rods are housed in the passage holes. For at least one rod, the passage hole of one of the annular flanges has a diameter greater than the diameter of the rod allowing the rod to move in case of deformation of one of the two conduits. An angle profile is inserted between the rod and a cylindrical portion adjacent to the annular flange and. is connected to the adjacent cylindrical portion through the intermediary of at least one means for absorbing eventual deformations in radial direction.

Abstract: A front attachment device for fastening a turbojet engine to an aircraft fixing strut. The attachment device is adapted to absorb the turbojet engine thrust loads, and includes a top bracket, and a lower bracket. A thrust load absorption vector results from a first convergence point of primary vectors passing through primary fixing points that couple the top bracket to the lower bracket and a second convergence point of secondary vectors passing through secondary fixing points that couple the lower bracket to the turbojet engine. The thrust load absorption vector transmits the turbojet engine thrust loads to the fixing strut, and extends along a longitudinal axis of the turbojet engine.

Abstract: A method of designing and manufacturing apparatus. The method comprises: creating a design space; analysing expected loads acting on the design space to calculate a first load path within the design space; analysing expected loads acting on the design space when the apparatus is in a damaged state to calculate a second load path within the design space; selecting a region of the second load path which falls outside the first load path; and creating a final design which includes: a primary structure falling within the first load path; and a damage indication feature falling within the selected region. The damage indication feature is designed to provide a visual indication when the load transmitted by the damage indication feature exceeds a threshold.

Abstract: An avionics equipment carrier system for slide-in modules with data processing, data transmitting, data storage or data displaying devices, such as for example electronics printed circuit boards, network components, storage devices, display devices and the like, or power supply devices, includes a housing, at least one module rack for accommodating the slide-in modules and at least one backplane board with Ethernet connection architecture. When the dimensions of the housing comply with ARINC standards, and the housing is arranged for installation in an avionics module rack as a quick-mount housing, and any desired circuit boards of a specific standard format can be used in the slide-in modules which are designed as quick-mount modules.

Abstract: The present invention provides a fuselage structure (1; 1?) of an aircraft comprising an annular skin segment (2; 2?) which has a cross-sectional opening (3; 3?), a pressure cap (4; 4?) for a pressure-tight closure of the cross-sectional opening (3; 3?), and a plurality of tension struts (7, 8, 9; 7?, 8?, 9?) which in each case connect the pressure cap (4; 4?) to the annular skin segment (2; 2?) and absorb loads acting on the pressure cap (4; 4?), as tensile loads. This advantageously means that the tension struts (7, 8, 9; 7?, 8?, 9?) do not have to absorb substantially any bending moments. Consequently, the tension struts can be produced with a relatively small cross section, which entails a reduction in weight. Furthermore, it is possible to produce and mount tension struts (7, 8, 9; 7?, 8?, 9?) of this type in a simple manner.

Abstract: A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

Abstract: A leak detector for detecting a leak in a line includes a transmitting device for generating radiation to be coupled into the line. By a receiving device, radiation that has emerged from the line through a leak is received, as a result of which the leak becomes detectable.

Abstract: The present invention relates to a method for producing a core structure. Firstly, a first core structure and a second core structure are fastened. The first core structure and the second core structure are positioned at a defined distance. A reinforcement element is introduced into a cavity between the first core structure layer and the second core structure layer. The reinforcement element, the first core structure layer, and the second core structure layer form a self-supporting core structure.

Abstract: An aircraft floor, and aircraft section provided with such a floor, and the utilization of such a floor in an aircraft section. The aircraft floor generally includes at least one central rail firmly mounted on a rigid structure of the aircraft, at least two lateral rails positioned on both sides of the central rail, and floor panels. Each lateral rail is connected vertically to the structure of the aircraft through a vertical connecting rod, each lateral rail being transversely free. Each floor panel is positioned between two adjacent rails, so that the transverse forces to which the lateral rails are subjected pass through the floor panels to the central rail.

Abstract: An arrangement for installing electric cables in the floor region of an aircraft includes longitudinal guide elements that form cable channels and essentially extend in the longitudinal direction of the aircraft parallel to seat rails that are arranged in the aircraft floor and serve for the mechanical attachment of seat legs. The longitudinal guide elements, which accommodate the data and supply cables to be installed, are not visible to aircraft passengers, but are still readily and easily accessible to the maintenance personnel. The floor plate features an elongate groove-shaped recess extending parallel to the seat rail in the longitudinal direction of the aircraft in the immediate vicinity of one of the two seat rails, wherein an elongate extruded profile is arranged in said recess. The extruded profile features an elongate drawer for transmitting shearing forces and an elongate cable shaft arranged above the drawer and serves for accommodating electric cables.

Abstract: The control panel (1) comprises two chains (A, B) of signal acquisition, digitization and processing, which are redundant and which include means (7) for performing crosschecks.

Abstract: A system is provided for non-contacting energy and data transmission from a first vehicle part to a second vehicle part. In this arrangement apart from a first inductive part in a hybrid transmitter for transmission of first data and energy an additional, second, data channel is installed in the first hybrid transmitter in such a manner that the second data channel is influenced as little as possible by the electromagnetic fields of the inductive part of the transmitter. To this effect a magnetic void can be created in the hybrid transmitters used. For the purpose of reception of not only the first data but also the energy and the second data a corresponding second hybrid transmitter is stated.

Abstract: A winglet comprising a root connected to a distal end of a wing; an upwardly angled section; a tip; and a transition between the upwardly angled section and the tip at which an outboard cant angle of the winglet decreases relative to a reference plane of the wing. In one embodiment the winglet is continuously curved and includes a point of inflection at which the span-wise curvature of the winglet changes sign. In another embodiment the upwardly angled section is planar. The winglet generates a tip vortex when in flight. The tip vortex is displaced outboard from the winglet due to the decrease in outboard cant angle at the transition.

Abstract: Disclosed is a pylon fairing for a turbine engine. The anterior portion of the pylon fair is attached to a turbine engine in a manner to absorb blows against the fan casing of the turbine engine in case of breakage of the fan blades of the turbine engine. The pylon fairing is configured with the turbine engine such that the anterior part of the pylon fairing is fastened to the engine's fan casing via a front fixing and a rear fixing. The rear fixing is affixed to the fan casing as relatively loose in order to absorb tolerances, and the front fixing is affixed to the fan casing and as flexible in at least approximately a radial direction with respect to the fan casing.

Abstract: A high lift system with a main wing and regulating flaps, also bearing devices for the mounting of the regulating flaps, and positioning devices for the positioning of the regulating flaps, wherein the respective bearing device and/or positioning device is at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least one inlet duct with at least one inlet, which device is located on or underneath the lower face of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet duct in a fluid-communicating manner, and has at least one outlet, which is located on the upper face in the region of at least one regulating flap of the high lift system.

Abstract: A method for plasma treatment and painting of a surface, the surface including a plurality of different materials includes blasting the surface with a carbon dioxide snow so as to activate the surface to improve an adhesive strength; and treating the surface with a plasma treatment using at least one plasma nozzle following the blasting step, the treating including guiding the at least one plasma nozzle at a distance of not more than 15 mm from the surface at a feed rate of not more than 50 m/min.

Abstract: A process for automatic generation of functional digital simulation of an electronic system starting from a wiring specification base, whereby the system includes equipment, at least one connecting wire interconnecting the equipment, optionally inputs/outputs to other systems, includes: creating a wire table TC by selecting and extracting data from the wiring specification base, the wire table TC including the reference of equipment it is connected to and the equipment category at least for each wire of the electronic system to be simulated and for each end of the wire; creating a simulation table TS by transformating each line of the wire table TC by using rules specific to each pair of pieces of equipment connected by each wire; and creating a computer code interpreted by a simulator, by transformating each line of the simulation table TS into a set of computer code lines according to the input and output equipment.

Abstract: An aircraft with at least two levels situated one above the other, including: a platform that can be moved between a first position and a second position, the first of these positions, as a lower position, being situated at a first level of the aircraft and the second position, as a higher position, being situated at a second level higher than that of the first level; an assembly of traction cables connected on the platform and a mechanism operating the cables for raising and lowering the platform; and an assembly of walls surrounding at least partially the platform and along which the platform moves.

Abstract: A ram air duct flap arrangement (22) comprises at least one ram air duct flap (24, 26) which is designed to close, in a closed position, a ram air inlet (14) or a ram air outlet (18) of a ram air duct (10) and, at least partly open, in an open position, the ram air inlet (14) or the ram air outlet (18) of the ram air duct (10). Furthermore, the ram air duct flap arrangement (22) comprises an actuator (32) for actuating the ram air duct flap (24, 26) between its closed position and its open position. A pressure control device (42) is designed to control a pressure (pi), which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an inner surface (44) of the ram air duct flap (24, 26) facing an interior of the aircraft, in such a way that it corresponds substantially to a pressure (pa) which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an outer surface (38) of the ram air duct flap (24, 26) facing the external environment.