Abstract: The present disclosure provides an actuator for an aircraft turbojet engine nacelle, which is interposed between a stationary front part of the nacelle and a moveable rear part of the nacelle. The actuator includes a main actuating arm, and a secondary actuating arm which axially extends from a rear section suitable for being connected on the moveable rear part of the nacelle, to a front section secured to a main nut screwed on a worm drive, in particular, the secondary actuating arm being designed for overcoming a breakdown of the main actuating arm.

Abstract: An assembly to hold an interface of a stationary outer structure of a nacelle and a casing of a jet engine includes first and second raised elements and two half rings. The first raised element belongs to an upstream end of the stationary outer structure, and the second raised element belongs to a downstream end of the casing. The first and second raised elements are formed so as to be placed in contact with each other, and the two half-rings are formed by a wall and an abutment. The wall defines a housing to receive the first and second raised elements when the casing and the stationary outer structure are mounted edge to edge, and the abutment is formed so as to keep the first and second raised elements in the housing.

Abstract: A thrust inverter for a turbojet engine nacelle includes an outer movable cowl and a front frame. The outer movable cowl translates between a closed position and a thrust inversion position and also moves to a supporting position in which the outer movable cowl is hinged and guided by a guiding member located on a pylon. In particular, the front frame holding cascade vanes is mounted downstream from an air blower housing, and part of the front frame is detachably connected to the air blower housing. The front frame is translatable along the guiding member once the front frame is detached from the air blower housing.

Abstract: A thrust reverser for a nacelle of a turbojet engine includes deflecting cascades and an external cowl which translates from a closure position to an opening position by a set of control cylinders being attached by their ends to the external cowl. The deflecting cascades are supported by a front frame and a rear frame respectively and are enclosed in an envelope formed by a fan carter and by a fan cowl. The thrust reverser further includes a lock which is able to connect or disconnect the deflecting cascades to the external cowl. When the lock is unlocked, the set of control cylinders translate the external cowl alone in downstream direction while in the lock position, the control cylinders translates the external cowl and the deflecting cascades together in downstream direction.

Abstract: An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural.

Abstract: The present disclosure relates to a turbojet engine nacelle equipped with at least one thrust reverser. The thrust reverser includes: two half-cowls forming an outer cowl which is articulated on hinges and translates between closed and open positions, a first actuator to translationally actuate a downstream frame, a second actuator to rotationally actuate each half-cowl, and a lock capable of locking or unlocking the half-cowls relative to one another. In particular, the thrust reverser includes cascades vanes supported at their upstream end by an upstream frame and at their downstream end by the downstream frame, and a connector between the downstream frame and the external cowl. The cascade vanes are enclosed in a shroud formed by a fan casing and a fan cowl.

Abstract: The invention relates to a jet engine nacelle reverse thrust device (10) including a means for diverting at least one portion of a jet engine air flow and moreover includes at least one cowl (20) that is translatable in a direction substantially parallel to a longitudinal axis of the nacelle, the device having at least one flap (30) that is pivotably mounted, by one end, onto the translatable cowl, said translatable cowl (20) being capable of passing alternately from a closed position, wherein said cowl, with the flap (30) in a retracted position, ensures the aerodynamic continuity of the nacelle and covers the diverting means, to an open position, wherein said cowl opens a passage in the nacelle and uncovers the diverting means, the flap (30) being in a pivoted position wherein it is capable of sealing off a portion of an annular channel of the nacelle.

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: The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion (15) is of the O-duct type and is capable of axial sliding between an operational position in which it covers the gas generator (3) of said turbojet engine and defines an annular cold-air jet with said hood, and a maintenance position downstream from said operational position. The downstream portion (15) is conformed so as to be capable of sliding without blocking relative to said gas generator (3), and the inner structure includes an upstream portion (13) that can be separated from the downstream portion (15) and that includes at least two doors (13a, 13b) capable of opening towards the outside.

Abstract: A thrust reverser for a turbojet engine nacelle includes a movable cowl, cascade vanes and a portion forming a movable variable nozzle. The cowl translates between a closing position and a maintenance position which is located beyond a thrust reversal position. In the maintenance position, the cowl opens a passage within the nacelle and allows access the inside of the nacelle. The variable nozzle is translated by an actuator between reduced ejection section and increased section positions. In particular, the cascade vanes move between retracted and active positions and are housed in an envelope formed by a fan casing and an outer cowl in the retracted position. In the active position, the cascade vanes are displaced downstream by an actuator through a passage open by the movable cowl in the nacelle. The actuator of the cascade vanes is dissociable from the actuator driving the variable nozzle.

Abstract: A suspension assembly for an aircraft turbojet engine includes a pylon and connecting rods for taking up the thrust of the turbojet engine which is connected to the pylon. In particular, the suspension assembly includes an insulator which is separate from the pylon and thermally insulates the connecting rods from the turbojet engine.

Abstract: A de-icing device for an aircraft nacelle includes two electric bands, and each of them is made from one main conductor oriented along a length of the band. In particular, the two electric bands have rectilinear elements and bent elements and are located on a same plane. Moreover, the two electric bands include spirals formed by association of several bent elements. Contiguous bands are embedded together in pairs, and the embedded bands are powered by different power supplies.

Abstract: A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

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: The thrust reverser includes a reverser cowl of which a downstream part of the reverser cowl forms a jet nozzle, cascade vanes fixed upstream from the reverser cowl, thrust reverser flaps, and an actuator. The thrust reverser is translatable under an effect of the actuator between a folded position of the thrust reverser flaps for operation of the nacelle in a direct jet mode, and a deployed position of the thrust reverser flaps for operation of the nacelle in a reverse jet mode. In particular, the stretching of the actuator results in causing a variation in a nozzle section of the jet nozzle as long as the stretching is below a predetermined value, and exposing the cascade vanes and deploying the thrust reverser flaps so as to perform the reverse jet mode beyond the predetermined value.

Abstract: An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural.

Abstract: This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.

Abstract: The present disclosure relates to a double-acting linear actuator for moving an inner part and an outer part of a cowl relative to a fixed frame. The linear actuator includes a first tubular body housing a first drive shaft and a second tubular body housing a second drive shaft. In particular, the first and second tubular bodies are mounted in series by the second drive shaft which is mounted on the first tubular body. The second drive shaft translates the second tubular body relative to the first tubular body when a lock of the first tubular body is in a locked position, and the first drive shaft translates both the first tubular and second tubular bodies when the lock is in an unlocked position.

Abstract: The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion (15) downstream from which is mounted at least one cowl (9) movable between a direct-jet position, in which the cowl (9) is aligned with the stationary portion (15), and a thrust-reversal position, in which the mobile cowl (9) is spaced apart from the stationary portion (15) so as to define an opening for the passage of a secondary flow (F), a means for deflecting (16) the secondary flow (F) through the passage opening, an actuator means (45) and a means (24) for guiding the mobile cowl (9) relative to the stationary portion (15), at least a first and a second adjacent cascade vane (13), positioned at an angle (B) relative to the movement axis (A) of the mobile cowl (9), arranged opposite the passage opening such that the deflected secondary flow (F) at least partially passes through the first and second vanes (13) in order to increase the deflection of said secondary flow (F) in the upstream direction, sai