Abstract: A method for alleviating and protecting loads of a lifting surface of an aircraft based on control of structural distortions of the lifting surface. The lifting surface includes a control surface, a maneuvering system for displacing the control surface and sensors which measure a dimensional characteristic linked to the distortion of the lifting surface. The method acquires characteristic data linked to the distortion of the lifting surface, determines a set of values of the shape, analyzes the value of the strain attribute and compares the set of values characterizing the shape to the values of the tolerance interval associated with the lifting surface. If the set of values characterizing the shape is outside of the interval, the process triggers an activation of the maneuvering system to displace the control surface from an initial position in order to alleviate the loads on the lifting surface.

Abstract: A nacelle for a turbofan including a mobile cowl mobile in translation between a closing position and an opening position, a window on the upstream side by a fixed cowl and on the downstream side by the mobile cowl, and a reverser flap in rotation between a closed position and an open position. The nacelle includes a locking system with a groove fixed to the mobile cowl and extending between a first end and a second end, and a guided element mounted guided in the slide and fixed to the reverser flap, the guided element moving from the second end towards the first end with cowl movement and leaving the groove when the reverser flap begins rotation, and the guided element moving outside the groove while the reverser flap pivots from the positions and entering the groove at the end of rotation of the reverser flap.

Abstract: A primary support strut structure and a method of manufacturing thereof for an aircraft power plant is disclosed having a first half-shell including a first free edge, and a second half-shell having a second free edge. The first half-shell and the second half-shell are assembled together by joining the first free edge and the second free edge so as to form a box-shaped structure. The two half-shell construction results in very rigid box structure, and a reduced number of ribs in the primary structure.

Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.

Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.

Abstract: A method of monitoring the clamping of an assembly by a threaded fastener. One element of the threaded fastener is rotated by a driver while the other is held stationary by a holding tool. The screwing torque and reaction torque of the holding tool are measured. Analyzing their evolution as a function of a third parameter makes it possible to determine accurately the pre-tension in the assembly. The disclosure herein further relates to a clamping method employing a real-time monitoring method of this kind. The disclosure herein also relates to a corresponding device for implementing a method of this kind.

Abstract: A method for assembling an aircraft pylon having a primary structure and at least one internal system at least partially positioned within the primary structure, wherein the internal system is positioned inside the primary structure before the last lateral panel of the primary structure is attached. The absence of one of the lateral panels facilitates the installation of the internal systems.

Abstract: A method for producing an acoustically resistive structure includes the steps of creating, consolidating and cutting a first layer of reinforcing fibres embedded in a first thermoplastic resin having a first melting point so as to obtain an interlayer, a step of laying a second layer of reinforcing fibres against a first face of the interlayer, a second consolidation step of consolidating the second layer of reinforcing fibres embedded in a second thermoplastic resin having a second consolidation temperature lower than the first melting point of the first resin so as to obtain a non-perforated external layer bound to the interlayer, a step of perforating the external layer and a step of laying an internal layer on a second face of the interlayer. An acoustically resistive structure obtained from the method as well as a sound-absorption panel including such an acoustically resistive structure are also described.

Abstract: The method for producing bindings includes: positioning at least one binding bobbin on a machine having: a winding bobbin including a device for supporting and a notch, an electric motor which is coupled to the winding bobbin; and at least one shaft capable of receiving a binding bobbin, supporting a free end of the binding of the binding bobbin on the winding bobbin, by the device for supporting; supplying electricity to the electric motor of the machine to drive the winding bobbin in rotation, so as to wind the binding of the binding bobbin over a plurality of turns around the winding bobbin; stopping the supply of electricity to the electric motor of the machine; and in the region of the notch of the winding bobbin, cutting the plurality of turns of bindings wound onto the winding bobbin.

Abstract: The disclosure herein relates to a quality control method and system in aeronautical manufacturing. The system comprises a tablet connected to a concession management server, the server being itself linked to an aircraft configuration database, a three-dimensional digital model of the aircraft and a fault database. The element to be inspected is identified using the digital model and the fault is characterized by browsing a predetermined decision tree associated with the element.

Abstract: An ultrasound probe for inspecting a bore opening onto a peripheral surface includes an offcentring device which includes at least two strips which are elastically deformable, connected to the ultrasound probe and configured to keep the emission head of the ultrasound probe pressed firmly against the wall of the bore that is to be inspected.

Abstract: A turbofan including a motor with a fan casing and a nacelle which includes a mobile cowl and a main slider bearing gratings and being mobile in translation between an advanced position and a retracted position in which the mobile cowl and the fan casing define, between them, a window. The nacelle also includes reverser flaps, each one being mounted articulated on the main slider between a closed position in which it obstructs the window and an open position in which it does not obstruct the window, a secondary slider mounted mobile in translation on the main slider between a first position and a second position, a transmission system configured to make each reverser flap pass from the closed position to the open position when the secondary slider passes from the first position to the second position, and a set of actuators that bring about a movement in translation of the main slider, and of the secondary slider.

Abstract: An aircraft includes a clearance between an opening and a door. The clearance communicates with a cavity and is oriented in a direction intersecting a flow direction of an air flow to the outside of the aircraft in flight. The aircraft further includes an upstream edge and an upstream outer surface situated in front of the clearance joined by a sharp edge with a bend radius of less than or equal to 1 mm, in order to limit the incidence of aerodynamic noise.

Abstract: A processor including computation groups, each computation group including computation cores, the processor being capable of simultaneously implementing a plurality of applications, each application being implemented by a computation core and possibly requiring a read-mode or write-mode access to an external memory connected to the processor. At least one core, called dedicated core, of at least one computation group is dedicated to management of the external memory, the management making it possible to temporally and spatially organize read-mode and write-mode accesses to the external memory of each application requiring a read or a write in the external memory implemented by the processor.

Abstract: A system for broadcasting an avionics temporal reference over a set of devices (7) of an aircraft, the system includes a master clock (5) configured to broadcast the avionics temporal reference via a wireless communication network (3) according to at least one predetermined frequency belonging to a wireless avionics intra-communication frequency band.

Abstract: An effector includes at least one contact surface configured to bear against a face of a workpiece near a zone of the workpiece that is impacted by a tool supported by the effector. The contact surface includes at least one interface made of a ductile material interposed between the contact surface and the face of the workpiece.

Abstract: An ultrasound probe for inspecting a bore opening onto a peripheral surface, includes a coupling support which has: a through-orifice to allow the ultrasound probe to pass through, a contact face, which has an external diameter greater than the diameter of the bore to be inspected and is configured to be pressed against the peripheral surface of the bore in order to close the bore.

Abstract: A method for assembling at least two parts, connected by main and secondary definitive connections arranged in predetermined positions, includes: secondary definitive connections each housed in secondary definitive holes passing through the parts to be assembled, made independently of one another before the parts are assembled, main definitive connections each housed in main definitive holes passing through the parts to be assembled, made during the same operation while the parts are held in place by the secondary definitive connections.

Abstract: An aircraft strut includes a primary structure which includes: a top stringer, a bottom stringer, at least one transverse frame which links the top stringer to the bottom stringer, a front end wall which links a front end of the top stringer to a front end of the bottom stringer, a rear end wall which links a rear end of the top stringer to a rear end of the bottom stringer, two lateral frames arranged on either side of the transverse frame, each lateral frame having a lattice form. An aircraft includes at least one strut described herein.

Abstract: An engine assembly with an electric motor that includes a cooling system of which a heat sink portion is arranged in an exhaust cone downstream of the fan driven by the electric motor, that is designed to effect thermal exchanges with a wall of the exhaust cone. Such an electric rear fan arrangement with boundary layer ingestion enables a cold air flow coming from the fan when the engine assembly is in operation to be used to cool the different components of the engine assembly.