In an air mobility vehicle, an engine operates as required to provide mechanical driving force or electric energy. A battery is charged with the electric energy from the engine. Main rotors operate using the electric energy of the battery and electric power generated by the engine to perform takeoff, landing, and cruising. Auxiliary rotors are disposed at or adjacent to the center of gravity of a vehicle body and mechanically connected to the engine via a clutch. The auxiliary rotors perform the takeoff, the landing, or the cruising by receiving the mechanical driving force from the engine when the clutch is in an engaged position. A controller monitors the states of the battery and the main rotors and controls the operations of the engine and the clutch.

A Short Takeoff and Landing (STOL) aircraft has a fuselage with an axis and an engine providing thrust, a first aileron at an end of a first wing, a second aileron at an end of a second wing, a first slot having a length through the first wing proximate the first aileron, orthogonal to the axis; a second slot having a length through the second wing proximate the second aileron, orthogonal to the axis; a first electric motor in the first wing driving a first two-blade propeller in the first slot, a second electric motor in the second wing driving a second two-blade propeller in the second slot, and a control mechanism enabling a user to drive the first and second electric motors in a same rotary direction, to reverse the rotary direction, and to drive the first and second motors at a same rpm.

A Short Takeoff and Landing (STOL) aircraft has a fuselage with an axis and an engine providing thrust, a first aileron at an end of a first wing, a second aileron at an end of a second wing, a first slot having a length through the first wing proximate the first aileron, orthogonal to the axis; a second slot having a length through the second wing proximate the second aileron, orthogonal to the axis; a first electric motor in the first wing driving a first two-blade propeller in the first slot, a second electric motor in the second wing driving a second two-blade propeller in the second slot, and a control mechanism enabling a user to drive the first and second electric motors in a same rotary direction, to reverse the rotary direction, and to drive the first and second motors at a same rpm.

A hybrid powertrain system includes an engine, an electric machine having a power shaft therein, and a clutch configured to releasably engage an output of the engine and the power shaft of the electric machine. The electric machine further includes an electrical output. The power shaft is configured to mechanically attach to and provide mechanical power to a propulsion device. A controller is configured to control the engine, the electric machine, and the clutch to implement one or more power output modes.

A hybrid powertrain system includes an engine, an electric machine having a power shaft therein, and a clutch configured to releasably engage an output of the engine and the power shaft of the electric machine. The electric machine further includes an electrical output. The power shaft is configured to mechanically attach to and provide mechanical power to a propulsion device. A controller is configured to control the engine, the electric machine, and the clutch to implement one or more power output modes.

A flap assembly for a fixed wing aircraft, comprising first and second flap portions, a compartments in the flap portions enclosing rechargeable batteries, motor controllers and electric motors, vertically-oriented slots in the first flap portion with propellers operable through a sidewall of the slot, such that the propeller in operation extends both over and under the top and bottom walls of the flap portion. With the flap assembly retracted in the wing the propeller is entirely enclosed in the length of the slot, and wherein the flap assembly is extended from the edge of the wing, enhancing area and curvature of the wing, increasing lift on the wing, exposing the slot, and with the slot exposed the motor is started spinning the propeller, providing increased airflow over the flap assembly, further increasing lift on the wing.

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 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 propulsor driven by the power source; and a wing extending from the fuselage, the vertical thrust propulsor positioned on or at least partially within the wing, the wing including a diffusion assembly, the diffusion assembly including at least one diffusion member fixed in position and located downstream of the vertical thrust propulsor for diffusing an airflow from the vertical thrust propulsor.

An aircraft defining a vertical direction and a transverse direction. The aircraft may include a fuselage, a wing extending from the fuselage, and a hybrid-electric propulsion system. The hybrid-electric propulsion system may include a power source, a plurality of vertical thrust electric fans arranged along the wing and driven by the power source, and a forward thrust propulsor. The power source may include a combustion engine and an electric generator. The combustion engine may also define a flowpath for exhausting combustion gases. The forward thrust propulsor may be selectively or permanently mechanically coupled to the combustion engine. The forward thrust propulsor may include a propulsor fan having a plurality of fan blades arranged outside of the flowpath of the combustion engine for exhausting combustion gases.