An electromechanical system for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine, and an electrical motor located at a second side of the firewall and configured to drive the mechanical component. The electrical motor mechanically connected to the mechanical component through a firewall opening in the firewall, the first side having a higher operating temperature than the second side. An electrical connection extends between the mechanical component and the electrical motor via the same firewall opening.

An abutment mechanism for a lift assembly of an aircraft. The abutment mechanism comprises a single rigid link having variable travel, the link comprising a rod and a body, the rod being movable in translation relative to the body along the longitudinal direction through said travel, the abutment mechanism including a movement member for adjusting an amplitude of the travel as a function of at least one predetermined parameter, the link having two endpieces suitable for being hinged respectively to a said lift assembly and to a said drive system.

An abutment mechanism for a lift assembly of an aircraft. The abutment mechanism comprises a single rigid link having variable travel, the link comprising a rod and a body, the rod being movable in translation relative to the body along the longitudinal direction through said travel, the abutment mechanism including a movement member for adjusting an amplitude of the travel as a function of at least one predetermined parameter, the link having two endpieces suitable for being hinged respectively to a said lift assembly and to a said drive system.

A cyclic pitch angle adjustment apparatus for a rotor or propeller and to a rotorcraft with such a rotor. The cyclic pitch angle adjustment apparatus may include levers that rotate rotor blades around associated pitch axes rods that mechanically link the levers with a bearing such that the rods are movable relative to the central point, the bearing being attached to a central rod that is movable and adapted for adjusting the cyclic pitch angle of the rotor blades from one pitch angle in one position to another pitch angle in another position.

A cyclic pitch angle adjustment apparatus for a rotor or propeller and to a rotorcraft with such a rotor. The cyclic pitch angle adjustment apparatus may include levers that rotate rotor blades around associated pitch axes rods that mechanically link the levers with a bearing such that the rods are movable relative to the central point, the bearing being attached to a central rod that is movable and adapted for adjusting the cyclic pitch angle of the rotor blades from one pitch angle in one position to another pitch angle in another position.

A rotary propulsion system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The rotary propulsion system includes an engine coupled to a freewheeling unit. A gear system positioned between the freewheeling unit and a proprotor assembly has a torque path coupling assembly disposed between an engine side gear assembly and a rotor side gear assembly. In a disengaged position, the torque path coupling assembly interrupts the torque path between the engine and the proprotor assembly. In an engaged position, the torque path coupling assembly completes the torque path between the engine and the proprotor assembly. A hybrid power unit is configured to accelerate the engine side gear assembly to match the output rotating speed to the input rotating speed enabling the torque path coupling assembly to shift from the disengaged position to the engaged position.

A rotary propulsion system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The rotary propulsion system includes an engine coupled to a freewheeling unit. A gear system positioned between the freewheeling unit and a proprotor assembly has a torque path coupling assembly disposed between an engine side gear assembly and a rotor side gear assembly. In a disengaged position, the torque path coupling assembly interrupts the torque path between the engine and the proprotor assembly. In an engaged position, the torque path coupling assembly completes the torque path between the engine and the proprotor assembly. A hybrid power unit is configured to accelerate the engine side gear assembly to match the output rotating speed to the input rotating speed enabling the torque path coupling assembly to shift from the disengaged position to the engaged position.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed is an adjustable propeller that may alter shapes during operation or rotation of the propeller such that the sound generated by the rotation of the propeller changes. The propeller may include multiple sections and joints that allow movement of the sections in any direction. Likewise, the propeller may include one or more sound flaps that may be opened or closed to further alter the sound generated as the propeller rotates.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed is an adjustable propeller that may alter shapes during operation or rotation of the propeller such that the sound generated by the rotation of the propeller changes. The propeller may include multiple sections and joints that allow movement of the sections in any direction. Likewise, the propeller may include one or more sound flaps that may be opened or closed to further alter the sound generated as the propeller rotates.

An intermeshing rotary-wing aircraft comprises a first rotary blade portion including a first blade and a second blade, a second rotary blade portion including a third blade and a fourth blade, a first shaft and a second shaft that transmit power to the first rotary portion and the second rotary portion and are symmetrically positioned at a predetermined angle, a first swash plate portion for controlling the first blade and the second blade, and a second swash plate portion for controlling the third blade and the fourth blade, wherein the first swash plate is coupled to three linkages, in which the coupled positions are located at the vertices of an equilateral triangle, the second swash plate has the same shape as the first swash plate, and the two equilateral triangles of the first swash plate and the second swash plate are star-shaped when horizontally moved and overlapped.