Abstract: A method of regulating the de-icing of a leading edge of an aircraft includes regulating the flow of air used for de-icing by at least a first regulator valve in accordance with two regulation levels, a first regulation level corresponding to the regulated position of the first regulator valve and a second regulation level corresponding to the fully open position of the first regulator valve. A de-icing device enables implementation of the regulation method.

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: A method of producing a panel for lining or cladding an aircraft interior, such as an aircraft cargo hold includes arranging at least one resin layer of a thermo-plastic polymer and at least one reinforcement layer of reinforcement fibres upon one another in a stack, wherein each resin layer extends adjacent and/or substantially parallel to each reinforcement layer; and consolidating the stack to form a panel by applying heat and pressure to the stack. The pressure is applied to the stack in a direction substantially perpendicular to a primary plane of the layers. The pressure is applied to the stack in a non-constant distribution over the primary plane. A corresponding panel for lining or cladding an aircraft interior, such as a cargo hold is also described.

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: 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: 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: 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: 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: 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: 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 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 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: 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 with a daylight input system may provide improved illumination with a reduced energy demand. The aircraft has a fuselage construction and at least one interior area arranged within the fuselage construction and includes the daylight input system. The daylight input system includes at least one light receiving device arranged in an outer wall, at least one light guiding device and at least one light emitting device arranged on the inner side. In this case, the light receiving device serves for receiving daylight present in the surrounding outside the outer wall and transmitting the same into the light guiding device. The light guiding device optically couples the light receiving device to the light emitting device. This light emitting device in turn emits the received daylight into an interior space on the inner side of a wall construction, wherein at least a partial deflection of the daylight is provided.

Abstract: A structural assembly comprising a first component having a ramped surface, and a fastener assembly for fastening the first component to a second component, the fastener assembly including a receptacle strip of resiliently deformable material attached to the ramped surface of the first component so as to assume the contour of the ramped surface, and a plurality of fastener receptacles attached to the receptacle strip for receiving respective fasteners. Also, a method of fastening a first component to a second component using the fastener assembly.

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: 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 pressure fuselage of an aircraft, which fuselage in longitudinal direction comprises several fuselage sections, wherein at least one rear dome-shaped pressure bulkhead is provided to form an aircraft-internal pressurized region, with a ring-shaped frame element profile being provided for radially outward attachment of said dome-shaped pressure bulkhead to at least one fuselage section, wherein the frame element profile on the side of the dome-shaped pressure bulkhead comprises a U-shaped profile section whose first end-side limb is attached towards the back on the dome-shaped pressure bulkhead by way of connecting means, and whose elongated radially outward extending second limb establishes a connection to the at least one fuselage section in such a manner that it is possible for the connecting means to be installed solely from the aircraft-internal pressurized region.

Abstract: The invention relates to an electrical power supply system for an aircraft comprising at least one main generator (20) feeding at least one technical load and at least one commercial load through at least one electrical power distribution channel comprising at least one electrical distribution busbar (21, 23, 25) and at least one voltage converter (22, 24, 26), wherein the grounding mode of at least one load is an IT type grounding scheme, with an isolated or high impedance neutral.