Abstract: The invention pertains to a composite panel with a first cover layer, a second cover layer and a first core layer that is arranged between the first cover layer and the second cover layer and features a plurality of cells that are separated from one another by walls at least in certain areas, wherein the first cover layer features a draining layer. The inventive composite panel may be distinguished from a composite panel according to the state of the art in that a second core layer with a plurality of cells that are separated from one another by walls at least in certain areas is arranged between the first cover layer and the first core layer.

Abstract: A connection arrangement for at least two abutting components to be firmly connected to one another, includes a self-piercing rivet having a rivet head for punching of a hole and subsequent riveting of the components, wherein a washer is allocated to the self-piercing rivet at the distal end region opposite to the rivet head, with the washer including a frontal area for the insertion of a circular indentation to create a firm compression connection between a hole in the washer and the distal end region of the self-piercing rivet.

Abstract: A system for evacuating persons from a vehicle includes a light signal generating device, which is adapted to emit at least one visual light signal that indicates at least one preset escape route for at least one person to be evacuated.

Abstract: A method of transmitting speech and digital data via an analog speech channel within a single frequency band, wherein an analog speech signal is transmitted via the speech channel and a stream of digital data is encoded by an encoding device to a sequence of blocks of symbols taken from a predetermined set of symbols. The transmission of the analog speech signal is periodically blanked during predetermined spaced time intervals, and the blocks of symbols are transmitted during the time intervals. In each time interval a plurality of signals are transmitted via a corresponding plurality of spaced predetermined carrier frequencies. A receiver receives the analog speech signal and the signals transmitted during the time intervals. The signals are demodulated to recover the individual symbols and the respective block of symbols transmitted during the time interval groups, and the digital data is recovered by decoding recovered blocks of symbols.

Abstract: The invention relates to a movable fastening unit for a seat frame in an aircraft. In said fastening unit, a connecting element can be movably mounted on both a seat structure and a floor fixture by means of bearings, thus allowing the seat frame to be moved relative to the floor fixture without having to detach the fixture from the floor.

Abstract: The method comprises the manufacture of a front section (2) and an rear section (3) with an assembly structure integrated into the rear section and the subsequent assembly of the two sections. The manufacture of the front section (2) comprises the manufacture of a main portion (9) of the front section separated from a coupling portion (10) of the front section. The assembly of the two sections comprises the assembly of the main portion (9) with the group comprising of the rear section assembly (3) and the coupling portion (10) of front section.

Abstract: The invention relates to a cabin system for an aircraft fuselage, having one or more lining components for interior lining, and optionally one or more cabin equipment components, wherein the lining component can be installed either separately or in combination with a further lining component and/or a cabin equipment component under tension in the aircraft fuselage such that a cabin that is under tension in the circumferential direction and attaches to the aircraft fuselage is defined. In this manner a passenger cabin configured as a closed safety cell is created in a fuselage, which is of particular advantage in an aircraft fuselage made of a fiber composite material because no splinters or the like can penetrate the self-supporting passenger cabin in case of damage to the same.

Abstract: A method for displaying information by means of a dual-view-display in a passenger-cabin of an air-/spacecraft, comprising the following steps: providing the dual-view-display on a predetermined portion of the passenger-cabin; providing first information by means of the dual-view-display, in such a way that said information can be perceived from a gangway between rows of seats of the passenger cabin; and simultaneously providing second information, different from the first information, by means of the dual-view-display, in such a way that said information can be perceived from one of the rows of seats. A display device for displaying information in a passenger-cabin of an air-/spacecraft, comprising a dual-view-display which is arranged on a predetermined portion of the passenger-cabin, the dual-view-display being configured to provide first and second information in the above described ways. A passenger-cabin for an air-/spacecraft comprising said display-device.

Abstract: An aircraft steering actuator has a driving shaft for connection to a drive source, the driving shaft defining a first axis, and a driven shaft for substantially perpendicular connection to a landing gear axle of an aircraft, the driven shaft defining a driven axis substantially perpendicular to the first axis, in which the driving shaft and driven shaft are connected in driving engagement by a ball-worm gear.

Abstract: A method for mounting an aircraft component, which in the mounted state is movable between a first and a second operating position and is taken up in its first operating position in a mounting area, comprises the measuring of the mounting area, in order to obtain data characteristic of the shape and/or the dimensions of the mounting area. The data characteristic of the shape and/or the dimensions of the mounting area are projected onto the aircraft component arranged in its second operating position. Finally, the aircraft component arranged in its second operating position is adjusted with reference to the projection of the data characteristic of the shape and/or the dimensions of the mounting area.

Abstract: A device for protecting piping from lightning. The piping includes tubular metal sections connected to each other by connection parts, a first portion of the connection parts being plastic material parts and a second portion of the connection parts being metal parts.

Abstract: Method of manufacturing “T” shaped stringers (1) with an angle different from 90° between the web (2) and the foot (3) whereby the “T” shaped stringers have a stringer web and a stringer foot. The method comprises, after placing together two hot-formed “L” shaped semi-stringers to form a “T” shaped stringer, placing the “T” shaped stringer inside an invar alloy angle leaving a gap between the stringer web and the invar alloy angle. Afterwards, a heating device (7) is moved over the stringer feet (3) surface and a roller (8) slides over said stringer feet (3) surface to adapt the geometry of the stringer feet to the geometry of the invar alloy angle. The resulting “T” shaped stringer is co-bonded on a cured skin with an adhesive line between the stringer and the cured skin, and finally the obtained “T” shaped stringer is cured.

Abstract: An aircraft engine assembly including a mounting pylon including a rigid structure fitted with a central box, together with a forward extension and a rear extension each including an attached upper organ supported on an upper surface of the central box, and an attached lower organ supported on a lower surface of the front end. The forward and rear extensions support at least a part of the first fasteners interposed between the rigid structure and a turbine engine.

Abstract: Method and device for an optimal management of the energy of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state and according to a management strategy, optimal commands of means (S1,S2, S3, S4, S5, S6) for controlling the energy of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given operational state.

Abstract: A display module for displaying passenger-specific display information in an aircraft, comprising: a display, a control unit, a storage device, and a first interface, wherein the first interface is connected to the control unit, and wherein the control unit is designed, on the basis of a signal that is present at the first interface, to read out a storage device content stored in the storage device and associated with the signal in relation to display information, and on the basis of the read-out storage device content and of the signal present at the interface to control the display.

Abstract: Method of manufacture of one or more pairs of components in composite material (11, 13; 11?, 13?) intended to form part of aerofoils located on both sides of the axis of symmetry of an aircraft whose shape has a conical tendency in the longitudinal direction, the angle of conicity being less than 10°, that comprises the following stages: a) Lay-up of layers on a flat tape lay-up table forming the laminate of a hypothetical component formed by all of the components of said pairs (11, 13; 11?, 13?), the components of each pair being arranged adjacently and the first components (11, 11?) and the second components (13, 13?) of each pair being arranged alternately, and the whole being arranged symmetrically relative to a hypothetical horizontal axis X-X of the tape lay-up jig; b) Cutting of the flat laminates corresponding to each of said components); c) Forming and curing said components.

Abstract: Embodiments of the disclosure include methods in which locations within an aircraft fuselage are automatically pointed to and marked so that a part may be fastened at each marked location. A mobile assembly includes a video camera that may capture images of the aircraft fuselage. A plurality of predetermined locations may be visualized and verified by a successive implementation of a first image recognition process and a second image recognition process. The mobile assembly may then automatically point to the predetermined locations after each has been identified and mark each predetermined location.

Abstract: An aerofoil wing with a main aerofoil, a high-lift flap movably arranged on the aerofoil wing by adjustment mechanisms. Each of the adjustment mechanisms including a first adjustment lever hinged to the main aerofoil via a first rotary linkage, with the formation of a first axis of rotation, a second adjustment lever hinged to the high-lift flap via a second rotary linkage, with the formation of a second axis of rotation, and a central linkage, with the formation of a third axis of rotation, such that the first, second and third axes of rotation pass through a common pole. The aerofoil wing further includes a drive device with a drive module mounted on the main aerofoil, and movable with respect to the drive module a drive lever coupled to the high-lift flap, and a stop device to limit the maximum extended setting of the high-lift flap.

Abstract: A method for the production of a stiffener on a surface of an element that is to be made rigid, whereby at least one of the two is made of a composite material that is not completely polymerized, whereby the stiffener includes—in a transverse direction—two contact zones with the surface between which the stiffener and the element to be made rigid form a cavity that empties out at least one of the ends of the stiffener, includes using a core that is placed in the cavity and removed from the cavity after polymerization. The core has a first part that has a low expansion coefficient to ensure the geometric precision required and at least one second part that has a significant elongation coefficient to make possible the extraction of the part by traction on one of the ends of the second part so as to cause a contraction of its cross-section.

Abstract: An aircraft fuselage element being a one-piece component, and including a closed wall defining an internal volume, an external surface of the wall forming the external skin of the fuselage. The wall has a cross section that includes on a side facing the internal volume a planar central part, a male connecting element at a first edge, and a female connecting element at its other edge, which connecting elements project, each connecting element configured to engage with the corresponding connecting element of another fuselage element placed side by side with the fuselage element to connect these fuselage elements longitudinally to each other, and one of the connecting elements includes a step forming a frame for the fuselage.