Abstract: A system for driving and guiding a trailing edge control surface arranged on a wing of an aircraft includes a first guide device attachable to the wing and coupled with an inboard section of the control surface for guiding the inboard section along a trajectory relative to the trailing edge region of the wing between a retracted position and an extended position, a second guide device attachable to the wing and holding a connecting means of an outboard section of the control surface, and a drive device attachable to the wing and the control surface for moving the control surface. The trajectory is a spatial path at least along one dimension, wherein a distance between the inboard section of the control surface and a fixed part of the wing changes during a motion of the inboard section on the trajectory.

Abstract: An aircraft aerodynamic surface (1) including a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) including a front spar (31) and a trailing edge (32) and a second control surface (4) having a front spar (41), a trailing edge (42), and a pivot device (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) including two lateral ribs (9, 9?), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which includes two lateral ribs (20, 20?), three internal ribs (17, 18, 19), two internal spars (24, 24?) and one internal spar (23).

Abstract: A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body configured to rotate around an axis parallel to the pintle axis of the hooking pintle. The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch in hooking engagement with the hooking pintle and to retain the door latch in a direction perpendicular to the door body in an overcenter position.

Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.

Abstract: An electrical power supply system for an aircraft includes a plurality of generators, each being couplable to and rotatable by an aircraft engine. and a plurality of electrical conversion units, each having a plurality of inputs and at least one output. Each generator includes at least four AC phases. The inputs of each individual electrical conversion unit are connected to a plurality of phases of at least two of the plurality of generators. The electrical conversion units each includes a rectification and conversion device for providing an output voltage having a predeterminable frequency and voltage level at the output.

Abstract: A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.

Abstract: A fixation assembly for affixing a first object to and variably spaced from a second object. The assembly comprises a male fastener and a female fastener. The male fastener comprises a bolt-shaped part having a circumferential outer surface. The surface includes alternately on a circumferential path, in a cross-sectional plane of the part, at least one ridged section and at least one plain section. The female fastener comprises a tubular part having a circumferential inner surface. The inner surface includes alternately on a circumferential path, in a cross-sectional plane of the part, at least one ridged section and at least one plain section. The male fastener can be inserted into the female fastener such that its ridged section coincides with the female fastener plain section. Either the male or female fastener is configured to be rotated relative to the other, thereby engaging respective ridges of the two fasteners.

Abstract: In operating an aircraft, a situation is displayed at each instant representing a spatio-temporal overview of risk zones around the aircraft. Each direction in space around the aircraft is scanned, and a simulated displacement of the aircraft in each direction is analyzed so as to identify potential zones of interference with the aircraft's path. Anticipated movement of risk zones over a planned time duration of a flight is determined. Such anticipated movement is correlated with an anticipation position of the aircraft over the planned time duration. Accordingly, risk zones initially appearing as a potential hazard may be determined to be safe by the time the aircraft reaches them, and vice versa. Such information is presented to pilots at an outset of the flight and continuously updated throughout the flight, enabling accurate and safe evaluation and strategy decisions.

Abstract: A sensor is fixed on an aircraft structure by a joining system which includes at least one enclosure in which is positioned at least one transducer, at least one passage configured to allow at least one conducting element to pass through the enclosure, at least one flexible connection connecting each transducer present in the enclosure to said enclosure and at least one binder joining together the enclosure and the structure. This joining system makes it possible to limit the spread of the deformations of the structure toward the transducer or transducers and ultimately the risks of malfunction.

Abstract: A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided.

Abstract: A method of measuring a surface of a liquid, the surface of the liquid having an edge which contacts a solid structure and an interior area which does not contact the solid structure. The surface of the liquid and the solid structure are illuminated with a pattern so that an upper part of the pattern is projected onto the solid structure to form an upper projected pattern and a lower part of the pattern is projected onto the interior area of the surface of the liquid to form a lower projected pattern. An image of the upper projected pattern is acquired and analysed to determine a height of the edge of the surface of the liquid. An image of the lower projected pattern is acquired and analysed to determine a characteristic of the interior area of the surface of the liquid.

Abstract: An auxiliary element (1) for the local deposition of fluid for a fluid dispenser header (10), includes a hollow main body (2), including a hollow conduit (3) inside the main body (2), configured such that the fluid flows through its interior, comprising an opening for the inlet of fluid (5) coming from the fluid dispenser header at one end, and a fluid outlet opening (6) at the opposite end, a cavity (4) located between the wall of the main body (2) and the hollow conduit (3), configured such that residual particles of the fluid flow through its interior, at least one connecting mean (8) to the interior of the hollow conduit (3) to the residual particles cavity (4) and an opening (7) located on the main body (2), configured for the outlet of residual particles from the cavity (4).

Abstract: A system for the control of the door assemblies of a bay of a landing gear of an aircraft, that is retractile and is able to be deployed, the opening of the bay for the landing gear being able to be closed by a forward door assembly and an aft door assembly, comprises a coupling mechanism of the forward door assembly and the aft door assembly, that is configured such that the aft door assembly is not completely closed, but is ajar, as soon as the forward door assembly is opened during the deployment of the landing gear and the aft door assembly is completely closed at the complete closing of the forward door assembly when the landing gear is retracted.

Abstract: A galley monument for an aircraft has a shelf structure, a pull-out member supported on the shelf structure so as to be able to be moved between an insertion position and a deployment position and has a carrier plate, and a display device supported on the pull-out member and having a display. A first surface of the carrier plate in the deployment position of the pull-out member is located in a deployment plane and protrudes with respect to the shelf structure and is located in the insertion position at least partially inside the shelf structure. The display device in the deployment position of the pull-out member can be pivoted about a centre of rotation between a storage position, in which the display device extends parallel with the deployment plane, and a position for use, in which the display device extends transversely relative to the deployment plane.

Abstract: An aircraft seat with a voltage supply port associated only with the aircraft seat and/or a data port associated only with the aircraft seat, a voltage supply unit, associated with the aircraft seat and including a voltage input and a voltage output, each of which is connected to another of the voltage supply ports, a switching circuit associated only with the aircraft seat and hooked up between the voltage output and the voltage supply port and/or between the data port and a data network, with which each of the voltage supply port or each of the data port can be activated or deactivated.

Abstract: A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

Abstract: An assembly system for an automated internal assembly on a curved assembly surface of an aircraft fuselage includes two assembly rails shaped in accordance with a curvature of the assembly surface such that they follow a longitudinal direction or a peripheral direction of the aircraft fuselage, so that the assembly rails are fastenable in the aircraft fuselage, along the longitudinal direction or along the peripheral direction of the aircraft fuselage, parallel to one another and parallel to the assembly surface of the aircraft fuselage; an assembly slide configured to slide along the assembly rails; and a tool supported by the assembly slide and configured to perform an assembly step; wherein the assembly slide has an assembly axis, along which the tool is movable relative to the assembly slide; and wherein the assembly axis is configured such that it follows the curvature of the assembly surface of the aircraft fuselage.

Abstract: A cabin arrangement for an aircraft, includes a galley monument, which has at least one projection surface, and a projector device by which graphical information can be projected onto the at least one projection surface. Furthermore, an aircraft is described which has at least one such cabin arrangement with the galley monument.

Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.

Abstract: A press for pressing a component, such as a thermoplastic consolidation and/or forming press, has a first fixed part as a first pressing tool, a movable part as a second pressing tool for pressing a component together with the first pressing tool, and a second fixed part for applying a pressing force to the movable part, wherein the second fixed part and the movable part apply the pressing force generated via interaction between a magnetic field of a pressing magnet and a superconductor cooled below its step temperature.