Abstract: A ducted fan turbojet including a nacelle including a fixed structure, a thrust reverser system having a frame, a mobile structure fastened to the frame, inner doors and outer doors hinged at the frame. The frame is mobile in translation on the fixed structure between a forward position and a rear position so as to define a window between the fixed structure and the mobile structure, the window being open between a bypass duct and the exterior of the nacelle. Each door is mobile between a stowed position and a deployed position and the mobile structure is assembled hinged on the frame via at least one hinge whose axis of rotation is globally parallel to a longitudinal axis of the ducted fan turbojet.

Abstract: A method for aiding in the piloting of an aircraft landing on a runway comprises determining current flight conditions of the aircraft, determining a first approach distance using the current flight conditions, determining a current aircraft position and selection of a first point on a cockpit screen that is a function of the current position of the aircraft, selecting a second point in proximity to the landing runway, and controlling the display on the cockpit screen, of a first circular arc centered on the second point and whose radius is a function of the first approach distance, the first circular arc intersecting at a third point with a straight line passing through the first point and through the second point and the length of a part of the first circular arc situated between the third point and a first end of the first circular arc, comprising a predetermined length.

Abstract: A turbojet engine comprising an engine, a nacelle comprising a fan case, an intermediate case having a part forming a hub and an outer shroud radially spaced away from the hub by a secondary, or bypass, flow path and fixed to the hub via arms, in which the outer shroud is situated to the rear and in the continuity of the fan case, a fixed structure fixed to the outer shroud, a mobile assembly mounted with the ability to effect translational movement on the fixed structure, and a ramp fixed to the outer shroud and configured to direct the secondary or bypass flow to exit the outer shroud. Such a turbojet engine makes it possible to simplify assembly and among other things, makes it possible to fix the ramp directly to the outer shroud.

Abstract: An aircraft nacelle comprising an air inlet, with a single fan cowling made of a single piece which extends over all the circumference of the fan. The fan cowling is borne by the air inlet and is mounted to be rotationally mobile about the axis of the nacelle relative to the air inlet, via a link and guiding arrangement comprising a circular rail and a runner capable of sliding along the circular rail. The fan cowling comprises one or more openings closed by hatches allowing access to the interior of the nacelle. The fan cowling has little susceptibility to being deformed both in flight and on the ground during maintenance operations. Furthermore, no pylon portion is needed in the zone of the fan cowling since the latter is not attached to the pylon.

Abstract: A joint for connecting a first aircraft structure to a second aircraft structure such that relative rotation and relative translational movement of the first and second aircraft structures along a first axis is permitted, whilst relative translational movement of the first and second aircraft structures along axes orthogonal to the first axis is substantially prevented. The joint includes a bracket having an opening aligned with the first axis; a pin aligned with the first axis and extending through the opening; and a bearing mounted in the opening. The bearing has an inner bearing surface defining a bore through which the pin extends, which is configured for translational sliding contact with the pin, and a part-spherical outer bearing surface configured for rotational sliding contact with the opening.

Abstract: Disclosed herein is a monobloc and removable pedal module for an aircraft rudder bar. The pedal module, which is intended for a rudder bar, includes a pedal, at least one integrated adjustment system, and a connection device which enables a removable connection of the pedal module to be produced. The pedal module is a monobloc component in order to simplify and facilitate its replacement via the removable connection obtained by the connection device.

Abstract: A nacelle having a window open between a secondary jet and the outside of the nacelle and comprising a fixed structure and a thrust-reversing system having a frame and outer doors articulated on the frame. The frame is translationally mobile on the fixed structure between an advanced position and a retracted position. Each outer door is mobile between a stowed position and a deployed position. The nacelle comprises at least one anti-vibration system which comprises a chock fixed to the fixed structure and having a hole, and a finger fixed to the outer door. The finger and the hole are configured so that the finger lodges in the hole when the frame is in advanced position. Such a nacelle makes it possible to limit the vibrations of the outer doors when they are in stowed position and before the mobile frame begins to be displaced to the retracted position.

Abstract: A turbomachine assembly comprising a nacelle having an air inlet and comprising a structure. A forward hood is fixed to the structure and extends backwards from the air inlet. An articulated hood is arranged in the upper part of the nacelle and at the rear of the forward hood and comprises a front edge arranged at the front of the articulated hood. A rear edge is arranged at the rear of the articulated hood. A joint is disposed at the front edge between the articulated hood and the structure and ensures a displacement of the articulated hood between a closed position and an open position. A locking system is arranged at the rear edge, and is mobile between a locked position and an unlocked position, where in the closed position, the front edge is under the forward hood.

Abstract: A bypass turbofan engine with a nacelle comprising a fan case and a thrust-reversal system. The fan case comprises an exterior wall, and the reversal system comprises a slider having an upstream frame, a downstream frame and a plurality of spars fixed between the upstream frame and the downstream frame, in which the slider is able to move between a forward position and a retracted position. The fan case comprises, at a rear edge of its exterior wall, a support. Each support comprises, for each spar, a shoe fixed to the exterior wall and positioned radially about the spar, and a skirt secured to the shoes and extending the rear edge, in which, in a forward position, the skirt bears around the downstream frame, and in which in a forward/retracted/intermediate position, the shoes are distant from the spars from the upstream frame.

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.

Abstract: A filling method for filling surface imperfections on a surface of a wing comprising a scanning step in which a control unit controls a movement of a scanner past the surface of the wing to scan the surface and transmit the collected data to the control unit, a computation step in which the control unit computes a digitized surface from the data, a determination step in which the control unit determines each surface imperfection by comparing the reference surface and the digitized surface, a generation step in which the control unit generates a digital model of the patch intended to fill the surface imperfection, and a printing step in which the control unit controls the movement of a 3D printer past each surface imperfection and commands the activation of the 3D printer in order to make it print the patch.

Abstract: A method for repair of a damaged stiffened panel of isogrid type, wherein the repair method comprises a step of removal of material with the aim of removing at least one damaged rib and also steps of fitting at least one structural reinforcement connecting at least two nodes positioned about the damaged zone and of at least one wall reinforcement connecting the wall of the stiffened panel and the structural reinforcement.

Abstract: A reference block for ultrasonic shear waves calibration, comprising slots, wherein the reference block has at least two different thicknesses, each thickness comprising two cavities with at least one slot being provided at each cavity. Preferably, the reference block comprises a plurality of steps, each step defining a different thickness.

Abstract: A nacelle comprising a fixed structure, a fixed cowl, a mobile cowl, and a motor arrangement to translationally displace the mobile cowl from a closed to an open position on the fixed structure. The nacelle comprises a window delimited between the fixed and mobile cowls and open between a secondary turbojet and the outside, a thrust-reversing door rotationally mobile about a rotational axis between retracted and active positions, and a driving mechanism which coordinates and defers the switch from the retracted to the active position with the switch from the closed to the open position. The driving mechanism comprises two connecting rods rotationally mobilely mounted on the fixed structure and bearing a wheel, a mobile cowl groove which slidingly receives the wheel, a guide integral to the thrust-reversing door, and a runner rotationally mobilely mounted between the connecting rods, as well as mounted to slide along the guide.

Abstract: A method for assisting in the piloting of an aircraft to observe a required time of arrival at a waypoint during a flight according to a predetermined flight plan comprising a nominal speed profile, comprising at least two flight segments, comprises the steps of determining an effective speed profile of the aircraft, and controlling by a guidance computer of the aircraft according to the effective speed profile. The step of determining an effective speed profile comprises the substeps of computing, for each segment of the nominal speed profile, a corrective term that is a function of a correction coefficient common to all the segments of the nominal speed profile, and computing, for each segment of the effective speed profile, a setpoint speed equal to the sum of a nominal speed of the nominal speed profile and of the corrective term.

Abstract: An aircraft has at least one cowling, a fixed structure, and a hinge system connecting the cowling to the fixed structure. The hinge system includes at least two hinges and at least two stops, including a first stop integral with the fixed structure and a second stop integral with the cowling, the first and second stops being configured to be in contact one against the other when the cowling is in the closed position and to ensure an absorption of a part of the loads between the cowling and the fixed structure at least along a direction perpendicular to the pivot axis of the hinge system.

Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

Abstract: A pilot's seat offering an evacuation device. The seat comprises a ladder fixed to the rear of the back and covered by a detachable cover associated with the seat and deployable between a storage position retracted inside the cover and a deployed evacuation position, in which case the cover is detached. Thus, the evacuation device is incorporated harmoniously into the seat which offers a solid base for the evacuation ladder.

Abstract: An airplane comprising a fuselage, two wings, a rear tail unit comprising a horizontal tail provided with two tail ends, and at least two engines arranged on the fuselage on either side of a vertical plane of symmetry of the airplane, the airplane having a longitudinal axis, the engines being mounted so as to be able to be displaced, at least in flight, on the fuselage, substantially parallel to the longitudinal axis, and the tail ends being mounted so as to be able to be pivoted, at least in flight, relative to the horizontal tail, the airplane thus having a configuration that changes in flight.

Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.