Abstract: A propulsion assembly of an aircraft comprising a turbojet engine with a front casing extending between a front face and a rear face, a mounting pylon having a primary structure with a front wall, and an engine mount having a first connecting rod and a second connecting rod, where one of the connecting rods is mounted in an articulated manner by a first connecting point on the front wall and by a second connecting point on the front casing, where the other of the connecting rods is mounted in an articulated manner by a third and a fourth connecting point on the front wall and by a fifth connecting point on the front casing, and where the connecting points are in the front third of the front casing.

Abstract: A propulsion assembly of an aircraft having a longitudinal axis and a vertical median plane and including a front cowling with a rear face perpendicular to the longitudinal axis, a primary structure with a front wall, and an engine attachment including a female yoke member rigidly attached to the front wall, a male yoke member rigidly attached to the rear face and mounted and articulated in the female yolk, a pin rigidly attached to the primary structure and the axis of which is parallel to the longitudinal axis, and a housing in the rear face in which the pin is housed, and wherein the yoke members, the pin and the housing are arranged at the level of the median plane.

Abstract: An aircraft propulsion assembly having a jet engine with a front casing, a primary structure with a lower spar, two outer rods, wherein each one has a rear end mounted in an articulated manner on the lower spar and a front end mounted in an articulated manner on the front casing, and two inner rods, wherein each one has a rear end mounted in an articulated manner on the lower spar and a front end mounted in an articulated manner on the front casing. Also an aircraft with such an assembly.

Abstract: An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave of a sound frequency, wherein the alveolar structure comprises at least one attached element, separate from partitions, and configured for vibrating at a frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.

Abstract: A propulsion system includes an engine, a pylon box, and a structural attachment. The engine includes an engine casing and an engine core. The pylon box has a front part and a rear part. The rear part is configured to attach the engine to an aircraft structure. The structural attachment has a front end configured to attach to the engine casing and a rear end configured to attach to the pylon which allows load transfer to the aircraft structure through the pylon box.

Abstract: A heat shield for protecting a part of an aircraft is disclosed including superposed layers providing thermal protection, and one or more layers providing fire protection. The heat shield also may include other layers implementing other functions.

Abstract: A propulsion system fastened to one side of an aircraft and having a longitudinal axis and a mid-plane and having a nacelle with two inner cowls, two outer cowls, two lower structural elements and two upper structural elements, wherein each outer cowl is articulated on a pylon by hinges with axes parallel to the longitudinal axis. The two outer cowls are contiguous at a separation plane containing the longitudinal axis and making, with the mid-plane, an acute angle. The axes are asymmetrical with respect to the mid-plane.

Abstract: An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave at a sound frequency, wherein the alveolar structure comprises at least one partition provided with at least one cavity configured such that the partition vibrates at a vibrational frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.

Abstract: An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave of a sound frequency, wherein the alveolar structure comprises at least one attached element, separate from partitions, and configured for vibrating at a frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.

Abstract: A propulsion system fastened to one side of an aircraft and having a longitudinal axis and a mid-plane and having a nacelle with two inner cowls, two outer cowls, two lower structural elements and two upper structural elements, wherein each outer cowl is articulated on a pylon by hinges with axes parallel to the longitudinal axis. The two outer cowls are contiguous at a separation plane containing the longitudinal axis and making, with the mid-plane, an acute angle. The axes are asymmetrical with respect to the mid-plane.

Abstract: A nacelle includes a thrust reverser having a cowl movable in translation and an ejection structure also movable in translation and forming with the cowl a moving assembly, the moving assembly configured to moved, alternately, into a closed position in which the ejection structure is inserted into a housing formed in the nacelle and the cowl closes an ejection opening in the nacelle, and an open position in which the cowl releases the ejection opening in the nacelle and the ejection structure is located in this ejection opening, the positioning of the ejection structure in the housing in the closed position making it possible, in particular, to make space in the ejection opening and to reduce the size of the thrust reverser.

Abstract: A heat shield including a main component and at least one secondary component for a part of an aircraft are disclosed including a main component adhesively bonded to the part and at least one secondary component secured removably to the main component. The main component and the secondary component are made from at least one material that simultaneously provides thermal protection and fire protection, therefore making it possible to obtain a heat shield that is particularly effective and includes at least one removable secondary component allowing access.

Abstract: A heat shield for protecting a part of an aircraft is disclosed including superposed layers providing thermal protection, and one or more layers providing fire protection. The heat shield also may include other layers implementing other functions.

Abstract: A nacelle for a jet engine having a selectively operated reverse thruster which redirects air flow to a cascade during a reverse thrust operation, the nacelle including a fancowl panel configured as a stationary partial cover for a jet engine; and a translating cowl panel configured to move transversely during a reverse thrust operation so as to expose a cascade for emitting reverse thrust airflow. In exemplary embodiments, a moveable automatic translating panel, or a rotatable hinge panel, or an extension portion of the fancowl is used to preserve clearance with an aircraft wing in a nacelle clearance area.

Abstract: The present disclosure relates to a thrust reverser device for a turbo jet engine nacelle including a fixed thrust reverser support structure having a longitudinal support half beam able to support a thrust reverser half-cowl, and the thrust reverser half-cowl mounted such that it can slide on the fixed structure in a direction substantially parallel to a longitudinal axis of the device via a guidance assembly, between a direct-jet position and a reverse-thrust position. In particular, the fixed structure includes a structure for offsetting the guidance assembly that guides the half-cowl circumferentially in a plane radial to the longitudinal axis between its various positions with respect to the half-beam on which the half-cowl is mounted.

Abstract: A nacelle for a jet engine having a selectively operated reverse thruster which redirects air flow to a cascade during a reverse thrust operation, the nacelle including a fancowl panel configured as a stationary partial cover for a jet engine; and a translating cowl panel configured to move transversely during a reverse thrust operation so as to expose a cascade for emitting reverse thrust airflow. In exemplary embodiments, a moveable automatic translating panel, or a rotatable hinge panel, or an extension portion of the fancowl is used to preserve clearance with an aircraft wing in a nacelle clearance area.

Abstract: The present disclosure relates to a thrust reverser device for a turbo jet engine nacelle including a fixed thrust reverser support structure having a longitudinal support half beam able to support a thrust reverser half-cowl, and the thrust reverser half-cowl mounted such that it can slide on the fixed structure in a direction substantially parallel to a longitudinal axis of the device via a guidance assembly, between a direct-jet position and a reverse-thrust position. In particular, the fixed structure includes a structure for offsetting the guidance assembly that guides the half-cowl circumferentially in a plane radial to the longitudinal axis between its various positions with respect to the half-beam on which the half-cowl is mounted.

Abstract: An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.

Abstract: The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material.

Abstract: A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal.