Abstract: A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions.

Abstract: A reverse thrust device and a system for actuating the reverse thrust device is provided by the present disclosure. The device includes at least one cowl that is translatably mounted in a direction substantially parallel to a longitudinal axis of a nacelle. The actuation system includes an actuation means that is capable of activating translational and rotational movement of the cowl and a panel of a nozzle. The actuation system also includes a downstream locking means for the nozzle and the cowl. The downstream locking means includes at least two reversible states, one of the states being a locked state in which the downstream locking means is suitable for locking the panel of the nozzle into a position for varying the section for outputting the nozzle with the cowl.

Abstract: A thrust reverser device is provided that includes movable thrust reverser cascades that move between a direct jet position and a thrust reversal position driven by a movable cowl able to be translated along the axis of an aircraft nacelle. The thrust reverser cascades cooperate with stiffening and sealing members of said thrust reverser device.

Abstract: The present disclosure relates to a self-mounted cascade for a thrust reverser of an airplane jet engine nacelle. The cascade includes an upstream portion and an opposite downstream portion, along with respective connection means so that two adjacent cascades are directly connected to one another only in the respective downstream portions by downstream connection means thereof. The downstream portion corresponds to an area extending from a downstream side edge over a length less than or equal to N times the length of the last cavity located along said downstream side edge, where N is less than 3. The present disclosure is of use in the field of airplane jet engine nacelles.

Abstract: A thrust reverser of a turbojet engine nacelle includes mobile cowls which retreat with respect to a front frame while causing via cylinders the tipping of the shutters initially folded inside these cowls, so as to substantially close an annular stream of cold air, and cascades disposed around the annular stream which receive the cold air flow in order to send it towards the front. In particular, the cascades are secured to the mobile cowls and slide.

Abstract: The invention relates to an assembly for a turbojet engine which includes a pylon (1) and a nacelle supported by said pylon (1). Said nacelle (3) includes a grid thrust reverser (21) including an integral cowl mounted so as to slide on rails (15), which are arranged on both sides of said pylon (1), between a direct jet position and a thrust reversal position. Said assembly is characterized in that it includes means (23, 31) for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon (1) and the cowl.

Abstract: The invention relates to a bent connecting rod (31) for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point (35, 38) that are designed so as to enable the pivotal movement of the connecting rod (31) relative to said first and second assemblies, respectively, the bent connecting rod (31) being suitably positionable such that the bend (40) is located upstream from said flow relative to said second pivot point (38), said second pivot point (38) being suitably built into the second movable assembly, characterized in that the bent connecting rod (31) includes at least two portions (33, 37) linked together by at least one self-aligning means (39a, 39b).

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: The invention relates to a thrust reversing device (20) that includes at least one mobile cowling (30) mounted in translation in a direction substantially parallel to a longitudinal axis of a nacelle, capable of moving alternatively from a closing position on which it enables the aerodynamic continuity of the nacelle into an opening position in which it opens a passage in the nacelle for the bypassed flow, wherein said mobile cowling (30) also includes as an extension at least one variable nozzle section (40) including at least one panel (41) mounted so as to be capable of rotation, the panel (41) being adapted for pivoting towards at least one position entailing a variation in the nozzle section (40) on the one hand, and pivoting towards a position in which it blocks a cold flow jet (13) formed between a fixed structure of a turbojet fairing (12 and the nacelle on the other hand, wherein the mobile cowling (30) and the panel (41) are associated with actuation means (50) capable of activating the respective t

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 tool assembly for manufacturing a part made of a composite material having a convex surface includes a mold. The mold at least partially defines the lines of the convex surface and is shaped so as to support, in a working position, drape-molding and polymerization operations for the part. In particular, the mold has a flexible portion alternating between the working position and a removal position where the mold is retracted relative to the working position.

Abstract: The present disclosure relates to methods for manufacturing a part made from a composite material by means of a drape forming operation as well as to a tool for implementing the methods. In particular, the part has at least one inner convex surface. The methods use at least one outer manufacturing mold and at least one intermediate mold. The inner surface of the outer manufacturing mold substantially defines outer lines of the part to be manufactured, and the intermediate mold is arranged opposite the inner surface of the outer manufacturing mold such that an inner surface of the intermediate mold at least partially defines the molding lines of an intermediate portion of the part to be produced.

Abstract: The invention relates to a nacelle (1) for a turbojet engine (8) comprising: an air intake structure (4) able to channel a flow of air towards a fan (7) of the turbojet engine (8), comprising an air intake lip (21) upstream of the nacelle (1) and attached at its ends to an outer panel (25) and an inner panel (23); a central structure (5) intended to surround said fan (7) and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity, said central structure (5) comprising a secondary, or bypass, flow path outer ring section (11) intended to surround the engine and a central outer cowl (13), and a downstream section (6), the outer panel (25) comprising a moving part (25a) attached to the air intake lip (21) and extending downstream of the inner panel (23) and at least one fixed part (25b) fixed to the central structure (5) or to the downstream section (6) and intended to nest together with the moving part (25a) through their having complementary shapes.

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: The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing, second connection means (24) for securing the one-piece propulsion unit to the plate and third connection means (7) for securing a pair of longitudinal handling members (22) to the plate. The invention also relates to a specific longitudinal member and to an installation including a one-piece propulsion unit secured in the plate.

Abstract: The invention relates to a nacelle for an aircraft engine that comprises a front cowling (13) and a rear cowling (1a), the rear cowling (1a) being mounted so as to slide between an upstream position defining a reduced nozzle (9) section and a downstream position defining an enlarged nozzle (9) section. The nacelle includes an intermediate member (25) arranged edge-to-edge with said front cowling (13), said member defining a housing (27) for receiving the upstream edge (11) of said rear cowling (1a) when the latter is in the upstream position.

Abstract: The present invention relates to a thrust reversal device (1) for a turbojet engine nacelle, characterized in that: (i) the movable cowl (3) is provided with at least one driving lead screw (30) having at least one peripheral groove over at least part of the length thereof, whereby said groove can engage with a stationary guide means (31) of the nacelle so as to rotate the lead screw during the translational movement of the movable cowl; and (ii) the lead screw is associated with at least one means for transmitting (32, 35, 36) the rotational movement thereof towards at least one drive system (33, 34, 25) of the flap.

Abstract: A cascade thrust reverser for an airplane dual flow jet engine nacelle is provided that includes a front frame holding a plurality of cascades, a cowling slidably mounted between a direct jet position and a reverse jet position. The cowl includes a substantially annular diaphragm that is placed edge-to-edge with the front frame and radially inside said cascades when said cowl is located in the direct jet position. Thrust reversal flaps are pivotably mounted onto the diaphragm, and cylinders for actuating the cowl are also provided. Upstream ends of the cylinders are mounted on a stationary portion of the nacelle, and the downstream ends of the cylinders are mounted on an upstream edge of the diaphragm.

Abstract: The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing (9) intended to surround the said fan and to which the air intake structure is attached, the latter structure having at least one peripheral interior panel (41), characterized in that the casing extends around the fan more or less as far as the fan blades (8), the air intake structure being connected to the casing by the interior panel by means of at least one structural peripheral flange (15) capable of providing containment for at least one blade should the latter break off.

Abstract: The invention relates to a nacelle including an air intake upstream from the jet engine (1), a medium section surrounding the fan of the jet engine (1), and a downstream section. The nacelle further includes at least one pair of mobile cowlings (3) provided on both sides of a vertical longitudinal symmetry plane of the nacelle and hinged essentially parallel to a longitudinal axis (A) of the nacelle so they can be opened to provide access to the jet engine (1). The mobile cowlings (3) are paired by fastening means (8) so that they can be hinged on each other about separate or overlapping axes (6). Each mobile cowling (3) comprises permanent connection means or means (14, 15) for connecting it temporarily by rotation and in closed position to a fixed structure (7) of the nacelle.