A ducted fan for an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan. The stator-side duct includes an inner wall facing the rotor-side fan and an outer wall averted from the fan. The ducted fan further includes a fastening device configured to support mounting of the ducted fan on a structural component of the aircraft. The fastening device includes a pin and a guide body. The guide body is configured to receive and guide the pin, the pin is insertable proceeding from the inner wall into a recess of the guide body, a first end of the pin protrudes relative to the outer wall, and the pin is configured to be mounted, via the first end, on a bearing of the structural component of the aircraft.

A ducted fan for an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan. The stator-side duct includes an inner wall facing the rotor-side fan and an outer wall averted from the fan. The ducted fan further includes a fastening device configured to support mounting of the ducted fan on a structural component of the aircraft. The fastening device includes a pin and a guide body. The guide body is configured to receive and guide the pin, the pin is insertable proceeding from the inner wall into a recess of the guide body, a first end of the pin protrudes relative to the outer wall, and the pin is configured to be mounted, via the first end, on a bearing of the structural component of the aircraft.

A vertical takeoff and landing aerial vehicle. A left linear support and a right linear support of the unmanned aerial vehicle are respectively provided with a first group of multiple lift propellers and a second group of lift propellers, and the aerial vehicle is provided with a left dorsal fin and a right dorsal fin. By arranging a plurality of lift propellers, a left dorsal fin, and a right dorsal fin on the vertical takeoff and landing aerial vehicle provided by the disclosure, the aerial vehicle is higher in stability in the flight process.

A power distribution system for an electric aircraft includes a first electric propulsion unit comprising at least two power stages; a first battery pack electrically connected to a first power stage of the at least two power stages; a second battery pack electrically connected to a second power stage of the at least two power stages; and a control system configured to control the first battery pack, the second battery pack, the first power stage, and the second power stage to transfer power from the first battery pack to the second battery pack through the first power stage and the second power stage.

A nonintegral cold plate is described for providing cooling of battery charging. The nonintegrated cold plate can receive and circulate coolant against a surface of a battery or of a vehicle. After charging the nonintegrated cold plate can be removed to save weight on the vehicle's payload.

A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.

A gyroplane employing torque compensated main rotor and hybrid power train is disclosed. The invention incorporates a torque-compensated main rotor system with a common Collective pitch control, which can be driven transiently during flight to allow Vertical Take-Off, Landing and Hovering (VTOLH) flight operations. Torque compensation is via a coaxial counter-rotating (CACR) rotor system, or alternatively using a single rotor in conjunction with one or more electronically-controlled, fixed-pitch, thruster motors. The use of electric motors for lift and torque compensation facilitates electronic and potentially autonomous control of all phases of vertical flight.

A ducted fan for an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan. The stator-side duct includes an inner wall facing the rotor-side fan and an outer wall averted from the fan. The ducted fan further includes a fastening device configured to support mounting of the ducted fan on a structural component of the aircraft. The fastening device includes a pin and a guide body. The guide body is configured to receive and guide the pin, the pin is insertable proceeding from the inner wall into a recess of the guide body, a first end of the pin protrudes relative to the outer wall, and the pin is configured to be mounted, via the first end, on a bearing of the structural component of the aircraft.

A ducted fan for an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan. The stator-side duct includes an inner wall facing the rotor-side fan and an outer wall averted from the fan. The ducted fan further includes a fastening device configured to support mounting of the ducted fan on a structural component of the aircraft. The fastening device includes a pin and a guide body. The guide body is configured to receive and guide the pin, the pin is insertable proceeding from the inner wall into a recess of the guide body, a first end of the pin protrudes relative to the outer wall, and the pin is configured to be mounted, via the first end, on a bearing of the structural component of the aircraft.

An aircraft includes: a gas turbine for driving a generator; a first electric motor for driving a first rotor; and a second electric motor for driving a second rotor. The gas turbine is arranged in a manner so that the gas turbine overlaps a rear wing in the front-rear direction of a fuselage, and a first high-voltage harness for transmitting electric power to the first electric motor and a second high-voltage harness for transmitting electric power to the second electric motor are arranged inside the rear wing so as to be separated from each other in the front-rear direction of the fuselage.