Abstract: An aircraft propulsion assembly has an engine casing, an attachment pylon, a first front engine attachment with a pin and a blade fitted on the pin and fastened in an articulated manner on either side of a median plane to the casing and a second front engine attachment with a central rod in the median plane fastened in an articulated manner to a lower wall of the attachment pylon and to a fitting of the casing. The central rod is generally parallel to a longitudinal axis. In this arrangement, the casing is brought closer to the attachment pylon for a saving in terms of height.

Abstract: An aircraft comprising at least one engine attachment system connecting a primary structure of a pylon and a motor, having a right-hand interface connected to the right-hand lateral face of the primary structure, a left-hand interface connected to the left-hand lateral face of the primary structure, first and second shackles connecting the right-hand and left-hand interfaces to the motor by virtue of engine connection pins and interface connection pins, a right-hand emergency connection pin cooperating with the right-hand interface and the motor, and a left-hand emergency connection pin cooperating with the left-hand interface and the motor.

Abstract: An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.

Abstract: A propulsion unit comprising an engine, a pylon, an engine mount system which connects a front part of the engine and the pylon, in addition to a suspension system which connects the pylon and a rear part of the engine which is offset toward the rear end of the engine relative to the engine mount system.

Abstract: A system for attaching a front engine of an aircraft, having: a vertical median plane, an engine pylon with a nose having a main female clevis, and a cylindrical housing around a vertical axis, a main link fastened to a front casing of the engine by a secondary ball-joint connection about a secondary axis perpendicular to the median plane by a secondary shaft, a main shaft, perpendicular to the median plane and forming a main ball-joint connection of the main link in the main female clevis about a main axis, the main and secondary axes in the plane perpendicular to the median plane, and an outer cylinder, coaxial with the vertical axis and a first end of which fastened in the cylindrical housing and a second end of which mounted, via an annular linear connection, around the vertical axis with respect to the front casing.

Abstract: A front engine attachment system for an engine having an engine pylon with a nose having a main female clevis and a cylindrical housing, a main rod fastened to the engine by a secondary ball joint connection about a secondary axis, a main shaft realizing a main ball joint connection of the main rod in the main female clevis about a main axis, wherein the main axis and the secondary axis are in the same vertical plane, a hollow outer cylinder with a vertical axis, of which a first end is fastened in the cylindrical housing and of which a second end is mounted so as to be able to move, via an annular linear connection, with respect to the front casing and an inner cylinder threaded and fastened in the outer cylinder.

Abstract: A front engine attachment system for an engine having an engine pylon with a nose having a male clevis and a cylindrical stud, two links that are fastened to the engine by a second ball-joint connection about a second axis, a first shaft establishing a first ball-joint connection of the links to the male clevis about a first axis, wherein the first axis and the second axis are in the same vertical plane, and wherein the cylindrical stud is mounted so as to be able to move, via an annular linear connection, with respect to the front casing.

Abstract: An engine pylon has a structure for fastening an aircraft engine beneath a wing and has two lateral faces. The structure has a tunnel laterally passing through it, between and through the lateral faces, and the engine pylon has a spreader housed in the tunnel and fastened in an articulated manner to each lateral face. A first end of the spreader has a first bore. A second end of the spreader has two second bores each forming a connection point with the engine. A rod is fastened in an articulated manner to the first bore and has two third bores each forming a connection point with the engine. Such an engine pylon has the ability to attach the engine, with reduced vertical bulk and with less drag.

Abstract: Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.

Abstract: The invention relates to an assembly between an aircraft pylon (30) and a turbomachine (20) of longitudinal axis (X), the pylon (30) and the turbomachine (20) each comprising front and rear longitudinal regions, the assembly comprising a rear support (40) configured to connect the rear region of the turbomachine (20) to the rear region of the pylon (30), the assembly being characterized in that the rear support (40) comprises a sliding pivot connection arranged between the rear region of the turbomachine (20) and the rear region of the pylon (30), so as to allow the turbomachine (20) only translational and rotational movements along and about the longitudinal axis (X) and along and about a vertical axis (Z) and a rotational movement about a transverse axis (Y).