Abstract: The invention relates to a nacelle (1) for an aircraft bypass turbojet engine comprising, in downstream cross section, an inner fixed structure (8) intended to surround part of the bypass turbojet engine and an outer structure (9) at least partially surrounding the inner fixed structure (8) so as to delimit an annular flow path (10), the outer structure (9) comprising at least one inner flap (101) positioned facing the annular flow path (10), an outer flap (103) not in contact with the annular flow path (10) at least partially surmounting each inner flap (101) in aerodynamic continuity with the rest of the outer structure (9), and an intermediate flap (105) positioned between each inner flap (101) and each outer flap (103), said intermediate flap (105) being capable of translational movement so as to increase or decrease the cross section of the annular flow path (10), and each inner flap (101) and each outer flap (103) being capable of rotational movement so as to remain in permanent contact with the interme

Abstract: A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.

Abstract: A cascade-type thrust reverser for an aircraft turbojet engine includes a front frame, a sliding cowl between a direct jet position and a reverse jet position, a plurality of actuating cylinders interposed between this front frame and this sliding cowl, and a plurality of cascades pivotally mounted on the front frame between the direct and reverse jet positions. In the direct jet position, the cascades are substantially parallel to the axis (A) of the thrust reverser, and in the reverse jet position, the cascades are inclined relative to the axis (A) of the thrust reverser. In particular, the cascade-type thrust reverser includes a single radial layer of cascades.

Abstract: A device is provided to drive flaps for an adaptive nozzle of a nacelle, and the adaptive nozzle includes at least one flap moveable in rotation and adapted to pivot toward a position causing a variation of a nozzle section. In particular, the device includes a control ring and a connecting rod driving the flaps. The control ring rotates along a circumference of the nacelle during a driving rod drives the control ring, and the connecting rod is connected to the control ring and one of the flaps so that the driving rod causes a displacement in translation of the connecting rod. The driving rod is connected to an assembly forming a lever, and the assembly is secured to the control ring.

Abstract: A method for controlling a position of a variable nozzle of an aircraft includes the following steps: setting the variable nozzle in a position P(t0) at a time t0 as a preliminary step; step A in which at each instant ti with 1<i<N, an optimal position P(ti) of the variable nozzle is determined according to magnitudes distinctive of the flight of the aircraft; step B measuring a time interval ?ti defined as a difference between ti and t0; and step C by which a displacement of the variable nozzle in a position corresponding to the optimal position P(ti) is authorized when the time interval ?ti is higher than a predetermined minimum threshold.

Abstract: A mechanism for coupling and uncoupling a motor inlet shaft and an outlet shaft, in particular, the inlet shaft is mounted in rotation on a front frame, and the outlet shaft is mounted in rotation on a rear frame. The outlet shaft rotates an outlet pinion, and the rear frame is slidably mounted to translate between a forward compact position and a backward deployed position. The mechanism includes a coupler, and first and second lockers to couple or uncouple the inlet and outlet shafts according to the translation of the rear frame between the forward compact position and the backward deployed position. The first locker locks in rotation the inlet shaft on the front frame, the second locker locks the outlet shaft on the rear frame. In particular, the second locker automatically locks the inlet and outlet shafts in rotation respectively, according to the displacement of the rear frame.

Abstract: A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.

Abstract: A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Abstract: A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin.

Abstract: A rear nacelle assembly for turbojet engine includes an inner structure surrounding a downstream portion of the turbojet engine. In particular, the inner structure is movable in rotation between an operating position in which it forms a downstream fairing and defines an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the inner structure moves away from the downstream portion. A suspension pylon is further provided to mount the thrust reverser cowl and the inner structure. The thrust reverser cowl slides between an opening position clearing air flow deviation grids and a closing position recovering the air flow deviation grids. Moreover, the thrust reverser cowl is mounted on the suspension pylon by a pivot connection sliding around a main axis, and the inner structure is mounted on the suspension pylon by a pivot connection around the main axis.

Abstract: An inner structure for a nacelle for an aircraft turbofan includes a plurality of active and passive movable portions. Each active movable portion can drive adjacent passive movable portions such that the inner structure has a nominal first position, a second position and a third position. In the second position, the active movable portions project beyond by the passive movable portions toward the outside of the inner structure after the active mobile portions have driven the passive mobile portions. In the third position, the active movable portions project beyond the passive movable portions toward the inside of the inner structure after the active mobile portions have driven the passive mobile portions. The present disclosure also relates to a nacelle having an outer structure and such an inner structure.

Abstract: An assembly includes a suspension pylon and a thrust reverser which has vanes for deflecting flow and a cowl able to move between an open position and a closed position by an actuator. The thrust reverser further includes rails able to slide in slideways. In particular, the actuator is disposed in line with a corresponding rail. The actuator may be an actuator having a rotating nut connected to an endless screw or an actuator suitable for pulling on the corresponding rail or on the corresponding slideway.

Abstract: The invention relates to a nacelle (1) for an aircraft bypass turbojet engine comprising, in downstream cross section, an inner fixed structure (8) intended to surround part of the bypass turbojet engine and an outer structure (9) at least partially surrounding the inner fixed structure (8) so as to delimit an annular flow path (10), the outer structure (9) comprising at least one inner flap (101) positioned facing the annular flow path (10), an outer flap (103) not in contact with the annular flow path (10) at least partially surmounting each inner flap (101) in aerodynamic continuity with the rest of the outer structure (9), and an intermediate flap (105) positioned between each inner flap (101) and each outer flap (103), said intermediate flap (105) being capable of translational movement so as to increase or decrease the cross section of the annular flow path (10), and each inner flap (101) and each outer flap (103) being capable of rotational movement so as to remain in permanent contact with the interme