Abstract: In a thrust reverser for an aircraft propulsion unit, the thrust reverser includes an internal fixed structure, a mobile cowl and blocking flaps. The thrust reverser also includes a first actuation mechanism that is configured to move the mobile cowl between a closing position and an opening position so as to cause the blocking flaps to move respectively between a retracted position and a deployed position, thus causing the thrust reverser to pass respectively between a full-thrust configuration and a thrust-reversal configuration. The thrust reverser also includes a second actuation mechanism that is configured to move the blocking flaps between the retracted position and a partially deployed position when the mobile cowl is in the closing position, so as to cause the thrust reverser to pass respectively between the full-thrust configuration and a reduced-thrust configuration.

Abstract: An aircraft propulsion unit includes a turbojet engine, a lateral pylon connected to the fuselage of the aircraft, and a nacelle on the lateral pylon. The nacelle includes an upstream section having an air intake, a downstream section housing a reverse thrust device, and a middle section having two fan half-cowls surrounding a fan housing of the turbojet engine, and when said half-cowls are in a closed position defining an aerodynamic continuity between the upstream and downstream sections. The fan half-cowls include a maintenance half-cowl positioned under the horizontal median plane of the nacelle, able to move between the closed position and an open position allowing access to the turbojet engine for maintenance operations on the turbojet engine. The nacelle further includes at least one standby lock, designed to hold the maintenance half-cowl in a position intermediate to the closed and open positions.

Abstract: A nacelle for an aircraft turbofan includes a rear section including a thrust reversal device having an upper door and a lower door, the upper and lower doors being mobile in rotation between a stowed position in which they are aerodynamically continuous with the rest of the nacelle and a deployed position in which the upper and lower doors are able to redirect forward the core and bypass flows produced by the jet engine, each door being moved from one position to the other by at least one dedicated actuator. The opening angle (X) of the upper door in the deployed position is smaller than the opening angle (Y) of the lower door.

Abstract: In a thrust reverser for an aircraft propulsion unit, the thrust reverser includes an internal fixed structure, a mobile cowl and blocking flaps. The thrust reverser also includes a first actuation mechanism that is configured to move the mobile cowl between a closing position and an opening position so as to cause the blocking flaps to move respectively between a retracted position and a deployed position, thus causing the thrust reverser to pass respectively between a full-thrust configuration and a thrust-reversal configuration. The thrust reverser also includes a second actuation mechanism that is configured to move the blocking flaps between the retracted position and a partially deployed position when the mobile cowl is in the closing position, so as to cause the thrust reverser to pass respectively between the full-thrust configuration and a reduced-thrust configuration.

Abstract: A thrust reverser includes two thrust reverser elements movable between a retracted position in which the thrust reverser is inactive and a deployed position in which the thrust reverser is active, a cylinder for deploying the thrust reverser elements, and a single-acting cylinder for retracting the thrust reverser elements.

Abstract: An air intake of a turbojet engine nacelle includes an air intake lip, an annular structure, a rear partition, and at least one acoustic attenuation structure. The annular structure includes at least a part of an outer fairing and an inner fairing joined to each other by the air intake lip. The rear partition is connected to the inner fairing. The acoustic attenuation structure is attached to the inner fairing of the annular structure. At least part of the outer fairing, the air intake lip and the inner fairing are integral with each other.

Abstract: A handling assembly of a propulsion assembly includes a frame which includes three radially spaced arms and is mobile in rotation about an axis transverse to a longitudinal axis of the handling assembly, and three branches for handling the nacelle, which are mounted transversally on the arms of the frame, extend along the longitudinal axis and include a working branch, which is movable between a rest position allowing a clearance with an inner wall of an air intake of the nacelle and a working position in which the working branch comes into contact with the inner wall, so as to exert a pressing force of the handling branches on the inner wall of the air intake. A method for handling a propulsion assembly using the handling assembly is also included.

Abstract: A lock for a cowl of a thrust reverser borne by a nacelle includes a striker fixed on the cowl, a hook that is configured to engage the striker and is elastically returned towards engagement with the striker, and a support fixed on the nacelle and supporting a locking/unlocking component interposed between the hook and the support. The locking/unlocking component is configured to allow, on the one hand, the hook to move in relation to the support between a locking position, in which the hook is engaged with the striker and exerts a pressure thereon, and a unlocking position, in which the hook is disengaged from the striker or is simply in contact therewith, and to allow, on the other hand, the hook to tilt in order to disengage it from the striker or engage it therein.

Abstract: An aircraft propulsion unit includes a turbojet engine, a lateral pylon connected to the fuselage of the aircraft, and a nacelle on the lateral pylon. The nacelle includes an upstream section having an air intake, a downstream section housing a reverse thrust device, and a middle section having two fan half-cowls surrounding a fan housing of the turbojet engine, and when said half-cowls are in a closed position defining an aerodynamic continuity between the upstream and downstream sections. The fan half-cowls include a maintenance half-cowl positioned under the horizontal median plane of the nacelle, able to move between the closed position and an open position allowing access to the turbojet engine for maintenance operations on the turbojet engine. The nacelle further includes at least one standby lock, designed to hold the maintenance half-cowl in a position intermediate to the closed and open positions.

Abstract: A thrust reverser includes two thrust reverser elements movable between a retracted position in which the thrust reverser is inactive and a deployed position in which the thrust reverser is active, a cylinder for deploying the thrust reverser elements, and a single-acting cylinder for retracting the thrust reverser elements.

Abstract: A nacelle for an aircraft turbofan includes a rear section including a thrust reversal device having an upper door and a lower door, the upper and lower doors being mobile in rotation between a stowed position in which they are aerodynamically continuous with the rest of the nacelle and a deployed position in which the upper and lower doors are able to redirect forward the core and bypass flows produced by the jet engine, each door being moved from one position to the other by at least one dedicated actuator. The opening angle (X) of the upper door in the deployed position is smaller than the opening angle (Y) of the lower door.

Abstract: The present disclosure relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a tranverse pivot in order to partially close off the air stream so as to guide it forwards, further including locks for locking the flaps in an intermediate opening position, between the closed position and the open position.

Abstract: An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors facing each other between two lateral beams. The doors pivot around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of the doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which the middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases. The edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody.

Abstract: The present disclosure relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a tranverse pivot in order to partially close off the air stream so as to guide it forwards, further including locks for locking the flaps in an intermediate opening position, between the closed position and the open position.

Abstract: An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors mounted facing each other between two lateral beams pivoting around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of said doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which said middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases, the edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody wherein each noise-reducing chevron formed on the middle portion of the downstream edge of a pivoting door is opposite an indentation in the middle portion of the other pivoting door in the direction perpendicular to said pivot direction, t

Abstract: Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inn

Abstract: A door for a thrust reverser of a nacelle of an aircraft being pivotally amounted on a fixed structure of the nacelle, in particular, the door being fitted with deflectors deflecting air flow is disclosed. The deflectors are arranged at an upstream end of the door and mounted such that they can move in a deflection plane perpendicular to the plane of the door. Each deflector is associated at its ends with an articulation arm capable of rotating about a pivot axis perpendicular to the deflection plane, allowing the deflectors to move in a straight line in the deflection plane. The present disclosure also relates to a thrust reverser system including the door and a fixed structure on which the door is pivotally mounted between a closing position and an open position.

Abstract: A thrust reverser with doors having at least one stationary structure is provided, on which at least one door is mounted pivoting between a closed position in which the door closes the reverser and makes up an outer cowling part, and an open position in which the door opens a passage in the stationary structure and can at least partially block a flow of air generated by a turbojet engine so as to reorient the door. The stationary structure includes at least two sets of cascade vanes that can be covered by the door when in the closed position.

Abstract: A door for a thrust reverser of a nacelle of an aircraft being pivotally amounted on a fixed structure of the nacelle, in particular, the door being fitted with deflectors deflecting air flow is disclosed. The deflectors are arranged at an upstream end of the door and mounted such that they can move in a deflection plane perpendicular to the plane of the door. Each deflector is associated at its ends with an articulation arm capable of rotating about a pivot axis perpendicular to the deflection plane, allowing the deflectors to move in a straight line in the deflection plane. The present disclosure also relates to a thrust reverser system including the door and a fixed structure on which the door is pivotally mounted between a closing position and an open position.

Abstract: Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inn