Hybrid aircraft propulsors having electrically-driven augmentor fans are disclosed. An example apparatus includes a turbofan having a core engine and a ducted fan to be rotated via the core engine. The ducted fan includes a plurality of ducted fan blades arranged circumferentially around the core engine and circumscribed by a nacelle. The example apparatus further includes an augmentor fan having an augmentor hub ring and a plurality of augmentor fan blades. The augmentor fan blades are arranged circumferentially around the augmentor hub ring and project outwardly relative to an outer surface of the nacelle. The augmentor fan is to rotate separately from the ducted fan. The example apparatus further includes an electrical drive to rotate the augmentor hub ring in response to a supply of electrical energy provided to the electrical drive.

The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).

A system includes an electronic speed control throttle input from which an anticipated electrical power demand is determined. The system includes a controller that determines a throttle input for a generator in order to satisfy the anticipated electrical power demand. The system includes an electronic speed control throttle output providing a delayed electronic speed control throttle signal.

A hybrid drive system driven by a gas turbine engine is disclosed. The hybrid drive system includes a planetary gear set, a first motor-generator, and a second motor-generator. The planetary gear set includes a first member, a second member, and a third member. The first member is operatively coupled to the second member and the third member. The first member is operatively coupled to and transmits power from a shaft of the gas turbine engine. The first motor-generator is drivingly coupled to the third member. The second motor-generator includes an output and is drivingly coupled to the second motor-generator by the second member and the third member. The hybrid drive system is configured to transfer the power from the shaft to the output of the second motor-generator.

The present invention relates to the technical field of unmanned vehicles. Provided is a hybrid-powered unmanned vehicle. The vehicle comprises: a fuel-combusting generator (10), a permanent magnet brushless DC motor (20), a chargeable battery assembly (30), an activation control circuit (40), an electronic speed adjuster, a flight controller, and a rotor blade. The activation control circuit (40) supplies power from the chargeable battery assembly (30) to the permanent magnet brushless DC motor (20) such that the permanent magnet brushless DC motor (20) drives an operation of the fuel-combusting generator (10) and then ignites and starts the fuel-combusting generator (10). When the fuel-combusting generator (10) is ignited and started, the control circuit (40) is activated to disconnect the supply of power from the chargeable battery assembly (30) to the permanent magnet brushless DC motor (20), while the fuel-combusting generator (10) drives the permanent magnet brushless DC motor (20) to generate power. The power generated by the permanent magnet brushless DC motor (20) can charge the chargeable battery assembly (30). A power output terminal of the permanent magnet brushless DC motor (20) and/or a power output terminal of the chargeable battery assembly (30) are used as a power output interface for a power supply device. When compared to using a battery as sole power supply device, the use of hybrid-power provides greater energy density of up to 1,000-1,500 Wh/kg.

A parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer neede

An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.

An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly moveable generally along a horizontal direction between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering at least one vertical thrust electric fan of the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the at least one vertical thrust electric fan when in the vertical thrust position.

An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan driven by the power source; and a wing extending from the fuselage. The vertical thrust electric fan is positioned on or within the wing, the wing including a diffusion assembly movable between a first position and a second position and positioned at least partially downstream of the vertical thrust electric fan when in the second position, the diffusion assembly including a first member and a second member, the second member movable generally along the vertical direction relative to the first member such that the first member and second member together define at least in part an exhaust flowpath for the first vertical thrust electric fan when the diffusion assembly is in the second position.

An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan oriented to generate thrust along a vertical direction and powered by the power source; and a wing extending from the fuselage and including the vertical thrust electric fan positioned at least partially therein. The wing includes a variable geometry assembly having partial wing assembly, the partial wing assembly including a frame and a first member, the partial wing assembly moveable generally along a longitudinal direction when the variable geometry assembly is moved between a forward thrust position and a vertical thrust position, the first member moveable relative to the frame to form an exhaust path for the vertical thrust electric fan.