Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.

Abstract: A device for locking an engine on a pylon includes two systems attaching the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine. A second region is adjacent to a center of gravity plane of the engine and closer to a fan than a first region. A first system attaching to the first region is rigid towards torsional, transverse and vertical engine forces. The first region is located at a separation between two compressors of the engine or two turbines, whether the fan is at a rear or front of the engine respectively, the separation being adjacent to a node of a first engine flexural mode. A second system attaching to the second region is rigid towards transverse and vertical forces but less rigid than the first system. The device also includes a third system withstanding thrust forces in the longitudinal direction.

Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Abstract: A rear part of an aircraft including a support structure for supporting engines, passing through the fuselage, through first and second openings. The rear part includes a connection structure connecting the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The first and second connection mechanisms each include at least one blocking element of the support structure, under compression loading by being applied to the casing and to the support structure.

Abstract: A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

Abstract: An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa.

Abstract: An engine is suspended from a main linear portion of a structure mounted on a fuselage or a wing surface of an aircraft. A connection includes flat symmetrical wings at an angle to one another, to support an attaching flange on which the engine is mounted, directly or through a mounting element. The flat shape of the wings makes them easy to manufacture, and enables them to resist the forces satisfactorily. The intermediate element resists overhang forces of the mounting satisfactorily. Flexible connections filter the engine's vibrations and prevent irregular forces being transmitted.

Abstract: An engine is mounted on a structure by an intermediate structure assembled by flanges, to the structure and to the engine, where a rigid structure connects the flanges. This arrangement enables design of the structure to be simplified while allowing a substantial overhang when it is sought to mount the engine by the plane of its center of gravity, while being obliged to move the mounting structure away from it. The intermediate structure is resistant to forces resulting from the overhang, and also allows assemblies that are favorable to a balanced transmission of forces to the structure and a satisfactory ability to filter vibrations.

Abstract: The present invention relates to an aircraft assembly (200) comprising a wing (2) and an engine attachment pylon (4) fixed to the wing by means of attachment means comprising a first and a second front wing system cleat (109, 109) connecting a rigid structure (108) of the attachment pylon and a front longeron (201) of the wing. The first front wing system cleat (109) comprises a first shearing pin (202) oriented in the transversal direction (Y) to ensure take-up of forces exerted in the longitudinal (X) and vertical (Z) directions of the pylon, and the second front wing system cleat (109) comprises a second shearing pin (208) oriented in the longitudinal direction (X) to ensure take-up of forces exerted in the transversal (Y) and vertical (Z) directions of the pylon.

Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Abstract: A method to mount an aircraft engine on a rigid structure of an engine mount, includes securing, on the structure, an attachment body for an engine attachment, the attachment body configured to lie against a contact surface of the rigid structure oriented forwardly, and secured to the structure by at least one shear pin passing through a first and a second primary orifice. The securing of the body includes: pre-positioning the engine relative to the engine mount to place the first orifice opposite the second orifice, and inserting a pin fitted with a convex centering head through the two orifices, so that the pin forms the shear pin.

Abstract: An aircraft engine assembly including an annular load-transfer structure surrounding the central casing and being mechanically connected to a plurality of substantially planar structures arranged externally with respect to the plurality of substantially planar structures, and biasing it at a plurality of load application points. At least one connecting rod is associated with each of the load application points, the connecting rod being positioned tangentially with respect to the casing, and including an inner end connected to this casing, and an outer end connected to the structure so that it has extending through it an imaginary plane in which the annular structure is located and extends through the load application point.

Abstract: An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including a second outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension.

Abstract: A rear part of an aircraft including a support structure for supporting engines, passing through the fuselage, through first and second openings. The rear part includes a connection structure connecting the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The first and second connection mechanisms each include at least one blocking element of the support structure, under compression loading by being applied to the casing and to the support structure.

Abstract: A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

Abstract: A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material.

Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.

Abstract: An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up thrust loads brought onto the fan frame, and arranged such that the third attachment passes through a first diametrical plane of the turbojet, the first and second attachments being disposed on one side and another of the first plane. The first and second forward engine attachments are respectively brought to the fan frame at two points, situated beyond the second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third attachment.

Abstract: An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including an outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the outlet of the heat exchanger system is provided on an outlet pipe connected to the exchanger and passing through a structural block fixed on a box, between the box and the engine.

Abstract: An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing.