Abstract: A jet engine nacelle has one thrust reverser device which includes a deflection means and one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle. The cowl can translate between a closed position and an open position. In the open position, the cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means. In the open position, the cowl opens a passage into the nacelle and uncovers the deflection means. The thrust reverser device moreover includes one blocking flap pivotably mounted by one end attached to a rear portion of the deflection means, and slidingly connected to the moving cowl. The pivoting end is also translatably connected to the rear portion of the deflection means.

Abstract: A longitudinal beam for a turbojet engine nacelle support structure is provided. The longitudinal beam is primarily made from composite materials and in the shape of an L and includes a longitudinal web contacting with an attachment pylon of the nacelle and a sole. More specifically, the sole produces a receiving part capable of cooperating directly or indirectly by embedding with an end of an associated front frame.

Abstract: A composite clevis connecting two parts includes composite clevis plies, an orifice to connect the two parts, and a ring defining the orifice. In particular, the composite clevis plies define a contour of the composite clevis, surround the ring and further define ribs connecting the ring to the contour of the composite clevis.

Abstract: The present disclosure relates to a structural part made of a composite material, such as a rail for a slidable cowl of a thrust reverser of an aircraft engine nacelle. The structural part includes a main portion made of a composite material and a reinforcing portion made of a composite material. The main portion defines a groove, and the reinforcing portion is provided at the bottom of the groove. In particular, the reinforcing portion defines a bearing surface at the bottom of the groove.

Abstract: A method for producing a one-piece preform for a composite structure includes the following steps: positioning a plurality of bundles of warp threads over two pairs of harnesses; making movements of low amplitude of each of the pairs of harnesses so as to make at least two adjacent and separate layers; and making movements of higher amplitude of the pairs of harnesses so as to at least partially link the at least two adjacent layers to an least one portion of the preform.

Abstract: A longitudinal beam for a turbojet engine nacelle support structure is provided. The longitudinal beam is primarily made from composite materials and in the shape of an L and includes a longitudinal web contacting with an attachment pylon of the nacelle and a sole. More specifically, the sole produces a receiving part capable of cooperating directly or indirectly by embedding with an end of an associated front frame.

Abstract: A nacelle for an aircraft engine is provided that includes a thrust reverser cowling slideably mounted between a direct jet position and a reversed jet position, an outlet jet pipe nozzle with variable cross-section positioned in a downstream extension of the reverser cowling, and means for respectively actuating the cowling and the nozzle. The nozzle is slideably mounted on the thrust reverser cowling, and the means includes at least one actuator for actuating said thrust reverser cowling, at least one driving pinion rotatably mounted on a fixed structure of said nacelle, and at least one rack for actuating the nozzle, secured to the nozzle and meshing with the driving pinion when the thrust reverser cowling is in the direct jet position, and escaping from this pinion when said reverser cowling is in the reversed jet position.

Abstract: The present disclosure relates to a device for linking a front frame of a thrust reverser to a fan casing, which includes a linking flange capable of engaging with a receiving part secured to the casing and an annular receiving part secured to the front frame. The linking flange is made up of two flange sectors, movably mounted around an axis, pivoting between an engaged position and an open position. In the engaged position, the flange engages with the annular receiving part of the fan casing and the annular receiving part of the front frame so as to connect them. In the open position, the flange is radially separated from the annular receiving part of the fan casing and the annular receiving part of the front frame.