A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and a front mount and a rear mount, the front and rear mounts being configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to a casing of the engine core and the front mount is located at substantially the same axial position as a centre of gravity (CG) of the gas turbine engine or forward of the centre of gravity of the gas turbine engine.

A front engine attachment system for an engine of an aircraft. An engine pylon has a frontal rib with a front engine attachment with a first link rod which is fixed directly to the frontal rib by two connecting points. A second link rod is provided which has a first end fixed to the first link rod by a connecting point. The first link rod is fixed directly to an engine casing by at least two connecting points and a second end of the second link rod is fixed to the engine casing by a third connecting point. The first link rod may be made up of two adjoining plates that are fixed together. Also, an aircraft with such a front engine attachment system.

A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and a front engine attachment having a beam that is fixed against the front face and to which is fixed, on either side of a median plane, a rod system, wherein each rod system is fixed to the beam in an articulated manner by at least one first connection point, and is configured to be fixed to a front part of the engine in an articulated manner by at least one second connection point. Such a front engine attachment system thus has rod systems having two rods, allowing the shape of the rods and the shape of the beam to be simplified.

An aircraft engine attachment including a beam fixed to a pylon and including a yoke with two walls, and a connecting rod with an articulation housed in the yoke, in which the connecting rod has a front flank and a rear flank which are facing inner faces of the walls. For each wall, a wearing part is disposed against the inner face of the wall and between the wall and the corresponding flank of the connecting rod. A Fixing arrangement ensures the fixing of the wearing part to the wall. Thus, the wearing parts prevent an excessive tilting of the connecting rod and the wearing of the connecting rod or of the yoke.

A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.

A strut assembly for a vibration isolation device is disclosed, comprising a piston spindle; a first elastomeric member and a second elastomeric member bonded to the piston spindle and in contact with an upper housing and a lower housing, respectively; a first strut support and a second strut support attached to or integral with the upper housing and the lower housing, respectively; a first strut spindle and the second strut support configured to be placed in the first strut support and the second strut support, respectively; and one or more removable struts configured to be engaged to the first strut spindle and to the second strut spindle, wherein at least one of the first or second strut spindles is removable such that the one or more struts can be replaced without breaking a bonding of the first elastomeric member, the second elastomeric member, or both.

An aircraft with folding mechanism, the aircraft including a fuselage, optionally a payload and/or landing gear attached to the fuselage, at least two longitudinal beams attached to the fuselage that preferably extend parallel to each other and parallel to a first aircraft axis, with lifting units attached to each of the longitudinal beams. At least one crossbeam is attached to the fuselage, and preferably extending parallel to a second aircraft axis and at right angles with respect to the longitudinal beams, with lifting units attached to the crossbeam. The longitudinal beams are rotatably attached to the fuselage by at least one respective first pivot joint configured for pivoting the longitudinal beams around a respective first pivot axis to a pivoted position. The crossbeam is rotatably attached to the fuselage, preferably by at least one second pivot joint, for pivoting the crossbeam around a second pivot axis to a pivoted position.

A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising: A standby protection device comprising a first connecting member fixedly mounted to the mast and a second connecting member fixedly mounted to the propulsion device, the second connecting member being rotatably hinged with respect to the first connecting member in at least one degree of freedom, and at least one retaining member keeping the second connecting member fixed with respect to the first connecting member, and configured, in the presence of a predetermined unbalance force on the propeller, to release the standby protection device in order to protect the mast.

A package delivery system uses unmanned aircraft operable to transition between thrust-borne lift in a VTOL configuration and wing-borne lift in a forward flight configuration. Each of the aircraft includes an airframe having at least one wing with a distributed thrust array coupled to the airframe. The distributed thrust array includes a plurality of propulsion assemblies configured to provide vertical thrust in the VTOL configuration and a plurality of propulsion assemblies configured to provide forward thrust in the forward flight configuration. A package delivery module is coupled to the airframe. A control system is operably associated with the distributed thrust array and the package delivery module. The control system is configured to individually control each of the propulsion assemblies and control package release operations of the package delivery module. The system includes a ground station configured to remotely communicate with the control systems of the aircraft during package delivery missions.

A seal for a wall of a vehicle includes a first plate that defines a first slot, and the first plate is to be coupled to the wall. The seal includes a second plate that defines a guide that extends outwardly from the second plate. The second plate is positioned adjacent to the first plate such that the guide is in communication with the first slot. The seal includes a third plate that defines a second slot that receives the guide, and the third plate is positioned adjacent to the second plate and is to be coupled to the wall.