Abstract: An acoustic attenuation panel for a propulsion assembly includes an acoustic front skin having perforations, and a central structure formed from partitions arranged perpendicularly in order to make up cells, wherein the front skin and the central structure form the panel which is made as a single piece and is provided for directly covering a surface of an element of the propulsion assembly forming a rear skin which closes the cells of the central structure at the rear.

Abstract: A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.

Abstract: A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.

Abstract: An acoustic attenuation panel for a propulsion assembly includes an acoustic front skin having perforations, and a central structure formed from partitions arranged perpendicularly in order to make up cells, wherein the front skin and the central structure form the panel which is made as a single piece and is provided for directly covering a surface of an element of the propulsion assembly forming a rear skin which closes the cells of the central structure at the rear.

Abstract: A locking device between a first structure and a second structure includes a bolt to lock the first and second structures, an indicator as to whether the bolt has locked/unlocked the structures, and a connecting system. The bolt includes a lock bolt attached to the first structure and able to engage a hook which is attached to the second structure. In particular, the connecting system connects the bolt with the lock bolt to the indicator, and the hook is mounted such that it can move between a first position in which it is engaged with the lock bolt and allows the indicator to be locked, and a second position in which the hook is free of the lock bolt and allows the indicator to be unlocked.

Abstract: The present disclosure relates to a seal for an aircraft turbojet engine nacelle thrust reverser, the seal having body having a cross section with respect to a longitudinal axis of the seal that is substantially circular, and a base which is intended to be mounted in a seal support. The seal is notable in that the base of said seal has apertures spaced from each other.

Abstract: The present disclosure relates to a seal for an aircraft turbojet engine nacelle thrust reverser, the seal having body having a cross section with respect to a longitudinal axis of the seal that is substantially circular, and a base which is intended to be mounted in a seal support. The seal is notable in that the base of said seal has apertures spaced from each other.

Abstract: The present disclosure relates to a holding assembly to hold a front frame of a thrust reverser to a turbojet engine casing. The assembly includes at least one connecting flange connecting the front frame to the turbojet engine casing, and also a system for locking the connecting flange. The system includes an actuating handle pivotally mounted on one of two facing ends of the connecting flange, and a connecting rod interposed between the other end of the two facing ends and a portion of the actuating handle. The system locks together the two facing ends, and the actuating handle includes a support provided with a groove and a screw for adjusting a free length of the groove. Furthermore, the connecting rod has, at its one end, an axis pivoting and sliding in the groove.

Abstract: A nacelle includes a front air inlet section, a mid-section and a rear section formed from two half-shells connected each other by a locking device actuated by a control handle equipped with a secondary locking system. The secondary locking system includes a blocking member to block the control handle in a locking position. In particular, the blocking member has a rod accommodated in the control handle and prolonged by a head. The blocking member and a region of the internal face of one of two cowls of the middle section come into abutment one against the other in order to prevent the closure of cowl if the control handle is not situated in its locking position.

Abstract: The present disclosure relates to an attachment device for a thermal protection panel, including an attachment base providing the attachment to a stationary structure that receives the panel, and that is provided with a fastening structure capable of penetrating a corresponding through-opening of the panel to be attached in order to engage with a corresponding retainer associated with a complementary retaining button. In particular, the fastening structure extends over a length greater than the thickness of the panel to be attached, such as to project from same, and the device includes an intermediate spacer arranged between the panel and the retaining button, and having a through-opening which the projecting portion of the fastening structure is capable of partially penetrating in order to engage with the means for retaining the button.

Abstract: The present disclosure relates to a holding assembly to hold a front frame of a thrust reverser to a turbojet engine casing. The assembly includes at least one connecting flange connecting the front frame to the turbojet engine casing, and also a system for locking the connecting flange. The system includes an actuating handle pivotally mounted on one of two facing ends of the connecting flange, and a connecting rod interposed between the other end of the two facing ends and a portion of the actuating handle. The system locks together the two facing ends, and the actuating handle includes a support provided with a groove and a screw for adjusting a free length of the groove. Furthermore, the connecting rod has, at its one end, an axis pivoting and sliding in the groove.

Abstract: A jet engine nacelle includes an air intake section, a middle section, and an aft section. The aft section is formed from two half-shells rotatably mounted such that they can each be deployed between a working position and a maintenance position under the action of a jack and a telescopic connecting rod each respectively having a first end fastened on the jet engine and a second end fastened in the corresponding half-shell. In particular, the nacelle includes at least one damping member arranged between each telescopic connecting rod and the corresponding half-shell, and the damping member is designed so as to be in a prestressed state when the corresponding half-shell is in the working position and can reduce vibration in the half-shell.

Abstract: The present invention relates to a locking device (10) designed to fixedly attach a first element (9a) to a second element, comprising a locking member (12) intended to equip the first element, an additional locking element intended to equip the second element, and a control handle (13) connected to the locking member via transmission means, characterized in that the transmission means comprise a telescopic connecting rod (15) designed to oscillate freely between a minimum extension position and a maximum extension position, and means for returning the telescopic connecting rod to its position of maximum extension, said return means being placed in a prestressed state when the control handle is in the closure position.

Abstract: A locking device between a first structure and a second structure includes a bolt to lock the first and second structures, an indicator as to whether the bolt has locked/unlocked the structures, and a connecting system. The bolt includes a lock bolt attached to the first structure and able to engage a hook which is attached to the second structure. In particular, the connecting system connects the bolt with the lock bolt to the indicator, and the hook is mounted such that it can move between a first position in which it is engaged with the lock bolt and allows the indicator to be locked, and a second position in which the hook is free of the lock bolt and allows the indicator to be unlocked.

Abstract: The present invention relates to a nacelle comprising a mid-section and an aft-section formed from two half-shells (9a) interconnected by a locking device (10) actuated by an operating handle (13) equipped with a secondary locking system comprising a latching member (19) for latching said operating handle in its locking position, said mid-section being formed from two cowls which can be deployed between a working position and a maintenance position, characterized in that the latching member and a region of the internal face of one of the two cowls are designed so as to butt one against the other in order to prevent the closure of said cowl if the operating handle is not situated in its locking position and/or if the latching member is not in its latching position.

Abstract: The present invention relates to a jet engine nacelle (1) comprising an aft section (8) formed from at least two half-shells (9) rotatably mounted such that they can each be deployed between a working position and a maintenance position under the action of a telescopic ram (11) and a telescopic connecting rod (12) each respectively having a first end (13, 14) fastened in or on the jet engine and a second end (16, 17) fastened in the corresponding half-shell, characterized in that it comprises at least one damping member (19) arranged between each connecting rod and said half-shell, said damping member being designed so as to be in a prestressed state when the half-shell is in the working position.

Abstract: The present invention relates to a locking device (10) designed to fixedly attach a first element (9a) to a second element, comprising a locking member (12) intended to equip the first element, an additional locking element intended to equip the second element, and a control handle (13) connected to the locking member via transmission means, characterized in that the transmission means comprise a telescopic connecting rod (15) designed to oscillate freely between a minimum extension position and a maximum extension position, and means for returning the telescopic connecting rod to its position of maximum extension, said return means being placed in a prestressed state when the control handle is in the closure position.