Abstract: A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.

Abstract: A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.

Abstract: A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap.

Abstract: A bolted joint for connecting a cover of an opening in a primary structure of a lifting surface of an aircraft to the primary structure. The bolted joint includes two first bolted joints on either side of a symmetry axis of the cover arranged without any lateral clearance, two second bolted joints on either side of the symmetry axis on the side of the cover opposite to that of the two first bolted joints, arranged without any lateral clearance in the holes of the primary structure and with a linear lateral clearance in the holes of the cover; a plurality of third bolted joints along the border of the cover arranged without any lateral clearance in the holes of the primary structure and with a radial clearance in the holes of the cover.

Abstract: A method for producing a curved profile from a rectilinear preform of preimpregnated fiber webs, including stacking webs on the deformable mandrel and winding the deformable mandrel and the stacked webs on a bending tool along an axis of rotation (X), the profile including a stack of N webs, at least one first part of the profile being positioned in a plane perpendicular to the axis of rotation (X) and at least one second part parallel to the axis (X) whereof a face can be in contact with the bending tool. The method includes stacking the N fiber webs on the deformable mandrel, generating a heat gradient between the face and the rest of the preform that is hotter than the face, bending, in a single phase, the N webs inserted between the deformable mandrel and the bending tool, and polymerizing the N bent webs.

Abstract: A locking device for an aircraft door in a fuselage section of an aircraft includes at least one fuselage fitting disposed in a region of a sill of the fuselage section and at least one door fitting disposed in a region of a lower edge of the aircraft door and corresponding in number to the at least one fuselage fitting. The at least one fuselage fitting and the at least one door fitting are each configured to transfer at least one of a circumferential load and a radial load.

Abstract: A method, and corresponding apparatus, for testing an aircraft control system is disclosed. The method includes simultaneously coupling a test device to a plurality of separate test points in an aircraft control system, selecting each test point individually such that the test device is enabled for electrical connection with the selected test point, conducting a test on the control system at each selected test point using the test device, detecting a signal or voltage at the selected test point, and indicating a result of the test at the selected test point to an operator.

Abstract: A ball-joint support for thin parts, through which a ball-joint is operably coupled to a thin part, and where the ball-joint includes an inner part with a central coaxial orifice through which a longitudinal axis is introduced, and an outer part that engages complementarily to the inner part is provided. The ball joint support includes a cap including a central through hole in which the ball joint is embedded inside via the outer part, and externally, the cap is embedded in a cylindrical opening included in the thin part, and mechanical means for axial retention of the thin part to the cap, wherein the thickness of the cap is greater than the thickness of the thin part where the cap engages.

Abstract: A weaving process for direct manufacture of three-dimensional structures with bidimensional walls with corners, without the need for sewing or other assembly between two ridges. The weaving is made by transforming weft threads into warp threads for making at least one face. The process is particularly adapted for the weaving of reinforcing elements for composite structures of corner fitting type.

Abstract: An interface device between an injection tube and a mold provided with an injection hole, wherein the interface device includes a terminal element for an injection tube, with an end piece inserted into one end of the tube and a sealing ring that slides onto the tube, and a mechanism for holding and clamping the terminal element. The mechanism which is to be screwed into a mounting that is rigidly connected to the mold and is arranged around the injection hole, forms a seal between an injection end of the end piece and a sealing surface of the mold at the injection hole. The dismantlable assembly includes a screw-on socket that has a supporting surface for the sealing ring.

Abstract: In a holder arrangement of an aircraft or spacecraft comprising a structural member, a holder comprising at least one lower part and at least one upper part is provided, and these are formed so as to be able to be clamped together to be attached with a non-positive fit to a fastening portion of the structural member. The fastening portion can be clamped between the lower part and the upper part. The holder arrangement is characterised by at least one fixing strip which can be connected to the fastening portion of the structural member in the longitudinal direction thereof and which comprises a fixing profile for fixing the holder to the structural member in the longitudinal direction of the structural member with a positive fit. An aircraft or spacecraft has at least one holder arrangement of this type.

Abstract: A system is provided for inerting a volume in a vehicle has at least one exhaust gas extraction point on at least one internal combustion engine of the vehicle, and exhaust gas line for routing exhaust gas from the exhaust gas extraction point to the volume, and at least one exhaust gas inlet on the volume for introducing exhaust gas to generate a low-activity environment in the volume. Precisely in vehicles with internal combustion engines, using exhaust gas for inerting a volume makes it possible to suggest an especially simple, cost-effective and robust solution to guard against the formation of an ignitable mixture in the volume or the like.

Abstract: A method for ensuring the safety of an aircraft flying horizontally at low speed includes an operation in which, when the flaps of the aircraft are disposed in a maximum extended position and are blown on by airscrews, the flaps are at least partially retracted, automatically, based on whether the thrust of the engines is at least equal to a predetermined lift value.

Abstract: A process for the production of a stiffened panel made of composite material includes the stages of depositing the fibers that constitute the panel on a rigid device, depositing at least one stiffener, covering the unit with a sealed wall, and then polymerizing, and providing—for each stiffener—a rigid counter-mold in contact with the convex surface of the stiffener, covering the zone(s) of the panel that is/are not covered by the stiffener with at least one band sufficiently rigid to transmit compression forces by allowing play between the band and the stiffener, and then depositing a seal such that the seal, the band, and the rigid counter-mold form the sealed wall, whereby the seal is able to have two states, a first malleable state during application so that it adapts to the profile of the lateral edges of the stiffeners, and a hardened state to ensure transmission of compression forces in a manner essentially identical to the rigid counter-molds or to the bands arranged on either side of the seal so as n

Abstract: A machining device has a machine head capable of displacement along at least three translation axes X, Y, Z for machining an immobile part fixed above the machining head. The machining head is maintained in a constant orientation by at least three articulated connecting rods. Two connecting rods define together with the machining head and with a first Y carriage, on which they are articulated, an deformable articulated parallelogram in the XZ plane. Another connecting rod is articulated on the machining head and on a second Y carriage and the second Y carriage is capable of displacement along Y on a second X carriage capable of displacement along X. The relative movement along X of the Y carriages results in a displacement in the Z direction. Several devices can be positioned in a plurality of tunnels, these tunnels being arranged so as to share several things.

Abstract: According to the invention, during take-off, the aircraft (AC) is given the tail strike attitude (?ts) and the ailerons (6G, 6D) are deflected fully downwards.

Abstract: An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mounted to an inner surface of the skin layer adjacent to the hole in the skin layer; and an access panel which covers the hole and can be removed to gain access to the gauge.

Abstract: A fuel piping connection device for aircraft includes a male end fitting and a female end fitting that are configured to engage one another. The male and female end fittings are made of a resistive material that is an insulating material loaded with conducting fibers. Each of the male and female end fittings is configured to be bonded to a radial outer wall at an extremity of a respective tube in the fuel piping or to a radial outer wall at an extremity of a respective piping connector. Each of the male and female end fittings includes an inwardly projecting shoulder configured to engage with an axial end surface of the respective tube in the fuel piping or with an axial end surface of the respective piping connector.

Abstract: A control device is provided for display means including several screens adapted for displaying several formats. The control device includes several command keys and means for automatic configuration of a command function for display of a format and visualization means associated with the command keys, adapted for respectively assigning to the command keys formats that can be displayed on a screen. The control device is usable in a cockpit of an aircraft.

Abstract: A connection assembly of an engine pylon underneath an aircraft wing, the wing being provided with a fitting, the engine pylon being provided with a fork joint nested in the fitting and fixed to the said fitting by means of a traversing pin system, including: an external primary pin, a secondary pin mounted inside the primary pin, a primary shoulder mounted directly around the primary pin, at a blind end of the pin system, to block the said pin in translation, a secondary shoulder mounted around one end of the secondary pin, at a blind end of the pin system, to block the system in rotation, and an interlocking assembly mounted around the primary pin and the secondary pin, at a free end of the pin system, to block the pin system in translation.