Abstract: A rail system for a vehicle includes a floor rail integratable into or onto the floor, first elongate movement rail elements, second elongate movement rail elements, holding devices to hold the movement rail elements on the floor rail, and gliders supportable on the movement rail elements in a gliding manner. The movement rail elements have a rail profile cross-section perpendicular to their main extension axis; the cross-section has an undercut that faces laterally outwards. The movement rail elements each have two opposed end faces, which can be brought into contact with end faces of other movement rail elements, such that at least one continuous movement rail with a constant rail profile cross-section is created. The gliders include a recess corresponding to the rail profile cross-section for gliding support.

Abstract: An apparatus for reducing brake wear having a brake de-selection function for selectively disabling at least one brake on a vehicle; and a controller. The controller is configured to receive torque information which relates to torque reacted by a brake on the vehicle during a braking event and wheel speed information which relates to a speed of a wheel associated with the brake during the braking event; calculate an energy input into the brake during the braking event, based on the received torque information and the received wheel speed information; determine whether the calculated energy input meets at least one predefined energy input criterion; and activate the brake de-selection function if the calculated energy input meets the at least one predefined energy input criterion.

Abstract: An acoustic treatment panel including a porous acoustically resistive structure which includes at least one external layer which is in contact with the external environment and which has through holes, internal strips including several openings which communicate with the inside of the cells of the panel and connecting canals, interposed between the external layer and the internal strips, which ensure that the floor-section openings communicate with at least one through hole of the external layer.

Abstract: In order to be able to determine with precision the location of the stagnation point at different zones along the leading edge of an aerodynamic profile, a system comprises rows of pressure sensors distributed on either side of the leading edge and forming, virtually, patterns that are spaced apart from one another in the form of simple polygonal lines, and a computer connected to the pressure sensors. The computer determines, along each of the patterns, a respective stagnation point position that is defined by a curved abscissa for which a pressure interpolated on the basis of pressure measurements provided by the pressure sensors of the corresponding row is at a maximum, and by an altitude evaluated on the basis of respective altitude data from the pressure sensors of the corresponding row.

Abstract: A method to control folding of a wing tip section about a fixed base wing section by a control system that automatically determines whether: (i) a command signal is received to fold the wing tip section, (ii) a first condition indicating signal indicates that the aircraft is on the ground; (iii) the current speed of the aircraft is no greater than a preset maximum speed, and (iv) the aircraft is not at gate in an airport.

Abstract: A wing comprising a fixed main part and a leading edge slat with upper and lower surface rear edges. The wing main part has an upper surface wall, which extends downstream and in alignment with the upper surface rear edge, and a lower surface wall, which extends downstream and in alignment with the lower surface rear edge. The wing has an upper surface gap between the end of the upper surface rear edge and the end of the upper surface wall and a lower surface gap between the end of the lower surface rear edge and the end of the lower surface wall. The wing has an upper surface channel downstream of the upper surface gap and a lower surface channel downstream of the lower surface gap. The wing comprises a suction system connected to each channel and arranged to suck the air contained in the channel.

Abstract: A grating for the formation of a reverse flow of a turbofan engine and comprising fins of a first type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the first type, fins of a second type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the second type. In this grating, each fin of one of the two types is inserted between two fins of the other type moving from forward to aft and the cord of the fins of the second type is smaller than the cord of the fins of the first type.

Abstract: A vortex generator control system for a controlling an aircraft vortex generator arrangement comprising a controller configured to receive one or more deploy or retract command signals from a flight control unit and further configured to send one or more command signals to a fluid control valve, a fluid pressure sensor configured to sense one or more pressure values from an actuator of the vortex generator arrangement and to signal the pressure value(s) to the controller, wherein the fluid control valve is configured to control fluid transfer between the actuator and a reservoir in response to a command signal from the controller.

Abstract: An assembly for an aircraft and comprising a wing comprising an airfoil box partly produced using a front spar, a mounting pylon arranged under the wing and comprising a primary structure formed as a primary box having a top spar extending at least partly under the airfoil box and having a slit, a bottom spar, lateral panels and a transverse reinforcing fixing rib, of which a bottom part is housed and fixed inside the primary structure and of which a top part passes through the slit. A fixing arrangement fixes the top part to the front spar. The fixing arrangement comprises a plurality of fixing bolts, where each fixing bolt fixes the top part to the front spar and has its axis at right angles to the fixing rib. Such an assembly allows the mounting pylon primary structure to be as close as possible to the wing.

Abstract: A holding device for an aircraft actuator, comprising a body that extends between a lug configured to hingedly connect the holding device to a actuator support body and an attachment flange configured to fixedly attach the holding device to a landing provided by a main body of an actuator. The holding device is configured to prevent movement of the actuator from a normal working position relative to the actuator support body in the event of structural failure of a connection body of the actuator.

Abstract: A sub-system 200 for an aircraft hydraulic system 20 that includes a first inlet 202 for receiving fluid from a supply 22 of hydraulic fluid, a system valve 210 for controlling fluid flow from the sub-system 200 to a hydraulically-operable system 24 of the aircraft hydraulic system 20, a check valve 220 for permitting fluid flow from the sub-system 200 and preventing or hindering fluid flow into the sub-system 200, a second inlet 240 for receiving fluid from a second supply 28 of hydraulic fluid, and a selector 230. The selector 230 configured to place the system valve 210 in fluid communication with the first inlet 202 when the selector 230 is in a first state, and to place the system valve 210 in fluid communication with the check valve 220 and the second inlet 240 when the selector 230 is in a second state different from the first state.

Abstract: A bypass turbojet engine comprising a fixed structure, a central core and a cowl comprising a fixed part and a mobile cowl mounted with the ability to rotate on the fixed structure between a closed position and an open position via hinges with gooseneck fitting. At least one hinge with gooseneck fitting comprises a gooseneck fitting having one end mounted in articulated manner on the mobile cowl and one end mounted in an articulated manner on the fixed structure, the bypass turbojet engine comprises anti-vibration means which are configured to exert pressure against the gooseneck fitting when the mobile cowl is in the closed position.

Abstract: An access cover for an aircraft hole that comprises a plurality of access cover holes, an inner surface, a plurality of first projections protruding from the inner surface, and a plurality of fixing elements configured to fix the access cover to a supporting structure of the aircraft hole. The fixing elements each comprise a male fixing element having an outer threaded surface, the male fixing element being configured to pass through a hole, and a locking element comprising a threaded hole and an extended portion, wherein the outer threaded surface of the male fixing element is configured to thread with the threaded hole of the locking element.

Abstract: A mobile satellite communication gateway includes an aircraft communication interface and a satellite communication interface. The aircraft communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a data network of an aircraft, while the satellite communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a satellite communication network. The satellite communication gateway includes a signal processing device, which is coupled to the aircraft communication interface and the satellite communication interface and which is designed to interchange data between the data network of the aircraft and the satellite communication network.

Abstract: A method for producing a fuselage portion, in particular for an aircraft or spacecraft, has the following method steps: welding a skin portion containing a thermoplastic material with a former containing a thermoplastic material in the region of a predetermined welding zone; and connecting an attachment element, configured as a crack stopper, to the skin portion and to the former in the region of the welding zone.

Abstract: A pole-shaped aircraft framework assembly including a first plug-and-turn connector forming a first end, a second plug-and-turn connector forming a second end, the second end opposite the first end, a first rod extending from the first plug-and-turn connector towards the second plug-and-turn connector, and a coupling component coupled to the second plug-and-turn connector for detachable coupling with the first rod. The first rod has a circumferential outer surface including alternately on a circumferential path in a cross-sectional plane of the first rod a ridged section and a plain section. The coupling component includes a tubular part having a circumferential inner surface including alternately on a circumferential path in a cross-sectional plane of the tubular part at least one ridged section and at least one plain section. One of the first rod and the coupling component is rotatable relative to the other one, engaging respective ridges of the first rod and the coupling component.

Abstract: A wing for an aircraft, comprising a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, allowing the slat to be moved between a retracted and at least one extended position. The assembly comprises an elongate slat track mounted to the main wing movably along a track longitudinal axis and connected to the slat. The wing has a compact connection assembly that does not require the front spar to be penetrated, in that the slat track is rotatably connected to the slat via a first hinge. The assembly further comprises a link element rotatably connected to the slat via a second hinge, and rotatably mounted to the main wing via a third hinge spaced apart from the second hinge. Also, a first axis of rotation of the first hinge is spaced apart from a second axis of rotation of the second hinge.

Abstract: An aircraft tailcone comprising a tailcone fuselage, a turbomachine, for example an APU, housed inside the tailcone, a ram air intake on the tailcone fuselage for the ingestion of ram air towards the interior of the turbomachine compartment, an inlet flap operable reciprocately from an open position in which ingestion of ram air is allowed, and a closed position in which ram air ingestion is prevented. The ram air intake extends annularly along a perimeter of the tailcone fuselage, and the inlet flap is configured such in its closed position that a surface of the inlet flap is substantially flush with the tailcone fuselage.

Abstract: A landing gear assembly (12) includes a primary load bearing strut including a shock absorber having a slider part (15) arranged to slide within a cylinder part (17). A link assembly (50) is attached between the slider part (15) and the cylinder part (17). A bogie (16) supporting wheels is mounted on the strut. The bogie may adopt different pitch angles. A pitch trimmer device (70) is attached to the bogie and to the link assembly, for example thus providing a relatively long moment arm (96) for control of the bogie pitch angle. The arrangement may be such that the pitch trimmer (70) is near mid-stroke as the aircraft achieves the full weight on wheels condition, whereas the pitch trimmer is at a fullest extent for flight case and for retraction. Onset of pitch trimmer closure/movement is used to detect the weight-on-wheels condition.

Abstract: A flight management assembly for an aircraft includes at least one flight management system and at least one display device, the flight management system configured to manage at least one flight plan of the aircraft and one long-term reference path of the aircraft. The flight management assembly additionally includes an auxiliary computer, the auxiliary computer being separate from and independent of the flight management system, the auxiliary computer linked to the flight management system and to the display device, the auxiliary computer configured to perform prediction computations to generate at least one short-term path, from at least the long-term reference path received from the flight management system and from current flight parameters of the aircraft and from piloting setpoints of the aircraft.