A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.

A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.

A rotorcraft having pusher propeller generated power during autorotations. The rotorcraft has an engine powered mode and an autorotation mode. The rotorcraft includes an engine and a drivetrain configured to receive torque and rotational energy from the engine in the engine powered mode. A main rotor system is coupled to the drivetrain and is rotatable to generate lift and forward thrust for the rotorcraft in the engine powered mode. A pusher propeller is coupled to the drivetrain and is rotatable to generate forward thrust for the rotorcraft in the engine powered mode. In the autorotation mode, the pusher propeller is aerodynamically driven responsive to airflow therethrough and the drivetrain is configured to receive torque and rotational energy from the pusher propeller, thereby providing power to the main rotor system.

A rotorcraft having pusher propeller generated power during autorotations. The rotorcraft has an engine powered mode and an autorotation mode. The rotorcraft includes an engine and a drivetrain configured to receive torque and rotational energy from the engine in the engine powered mode. A main rotor system is coupled to the drivetrain and is rotatable to generate lift and forward thrust for the rotorcraft in the engine powered mode. A pusher propeller is coupled to the drivetrain and is rotatable to generate forward thrust for the rotorcraft in the engine powered mode. In the autorotation mode, the pusher propeller is aerodynamically driven responsive to airflow therethrough and the drivetrain is configured to receive torque and rotational energy from the pusher propeller, thereby providing power to the main rotor system.

An aircraft is described comprising a transmission unit with a first module and a lubrication system; the first module comprises a casing and a movable member; the lubrication system comprises a header, a nozzle fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing of the first module, a collection tank for the lubricating fluid injected by the nozzle, and recirculation means designed to cause the recirculation of the lubricating fluid from the collection tank to the feed header; the first module comprises a valve available in a first configuration, in which it enables the outflow of said lubricating fluid from said module to the recirculation means when the pressure of the lubricating fluid inside the header is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module from the recirculation means when the pressure of the lubricating fluid inside the header is less than the threshold value.

A multicopter comprises: a support; rotors supported by the support; an internal combustion engine supported by the support; a generator supported by the support and driven by the internal combustion engine to generate power; electric motors supported by the support, supplied with electric power from the generators, and configured to drive the rotors; and a circuitry that control a flight of an aircraft by individually adjusting a rotational speed of each of the rotors. The multicopter also comprises a plurality of the internal combustion engines or a plurality of the generators.

A multicopter comprises: a support; rotors supported by the support; an internal combustion engine supported by the support; a generator supported by the support and driven by the internal combustion engine to generate power; electric motors supported by the support, supplied with electric power from the generators, and configured to drive the rotors; and a circuitry that control a flight of an aircraft by individually adjusting a rotational speed of each of the rotors. The multicopter also comprises a plurality of the internal combustion engines or a plurality of the generators.

A multicopter is provided with: a support; multiple rotors provided to the support; an engine which is provided to the support and capable of varying the output thereof; an electric generator which is supported by the support and generates electricity by being driven by the engine; a capacitor which is provided to the support; multiple motors which are provided to the support, which are configured to be capable of supplying electricity from the electric generator and the capacitor, and which drive the multiple rotors respectively; a flight controller which controls the attitude of the multicopter main body by adjusting the revolving speeds of the respective rotors; and a power plant controller which controls the electric power to be generated by controlling both the engine and the electric generator in accordance with a control instruction given by the flight controller.

A multicopter is provided with: a support; multiple rotors provided to the support; an engine which is provided to the support and capable of varying the output thereof; an electric generator which is supported by the support and generates electricity by being driven by the engine; a capacitor which is provided to the support; multiple motors which are provided to the support, which are configured to be capable of supplying electricity from the electric generator and the capacitor, and which drive the multiple rotors respectively; a flight controller which controls the attitude of the multicopter main body by adjusting the revolving speeds of the respective rotors; and a power plant controller which controls the electric power to be generated by controlling both the engine and the electric generator in accordance with a control instruction given by the flight controller.

A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance. The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.