Hyundai Motor Company

Kia Corporation

Kia Motors Corporation

Hyun Woo Jun

Hee Kwang Lee

Woo Suk Jung

Hyun Seok Hong

Gwi Taek Kim

Hyun Ki Cho

Keun Seok Lee

Jae Hyung Kim

Yoon Cheol Jeon

Se Hwan Park

A hybrid air mobility vehicle can make a long-distance flight through an efficient operation of an engine and a battery, and can reduce discomfort by reducing noise according to flight surroundings. The hybrid air mobility vehicle includes: an engine and a generator; a battery and a drive motor electrically connected to the generator; a first propeller connected to the drive motor and a second propeller connected to the generator through a clutch; and a controller that controls driving of the engine, the clutch, and the drive motor, based on a flight factor including at least one of a flight mode, a required power, a battery charging amount, or a surrounding flight environment of the hybrid air mobility vehicle.

Hybrid air mobility vehicle

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.

Air mobility vehicle

An air-cooled battery cooling system for an air mobility vehicle may ensure the cooling performance for batteries using air flows during the flight of the air mobility vehicle, since the cooling of the batteries is performed using an air flow in the top-bottom direction due to the hovering of the air mobility vehicle and an air flow in the front and rear direction due to the cruising of the air mobility vehicle, the efficient cooling performance for the batteries is ensured in a variety of flight modes. Furthermore, the batteries are securely fixed while being cooled by air flows via the heat transfer pads within the battery packs.

Air-cooled battery cooling system for air mobility vehicle

An oil dispersion system uses an actuator for propellers and includes a pumping device that circulates oil when a driving motor is operated to drive a propeller, whereby the propeller and an oil circulation structure are integrated, and a circulation amount of oil is adjusted based on an angle of a swash plate of the pumping device when the driving motor is operated in order to drive the propeller, thereby controlling a supply of oil to no more than that required by oil-using parts.

Oil dispersion system using actuator for propellers

A power management system for an air mobility vehicle includes a plurality of batteries configured to provide power to a propulsion unit of the air mobility vehicle to propel the air mobility vehicle, and a discharge control unit configured to monitor an operation state and a charge state of each battery, determine a discharge mode of each of the plurality of batteries according to the monitored operation state and the monitored charge state, and control whether each of the plurality of batteries is discharged or a discharge rate thereof according to the determined discharge mode.

Power management system for air mobility vehicle and operation method thereof

A magnetic gear may include a stator, having a stator core having a plurality of teeth extending toward a rotation shaft and a plurality of coils wound around the plurality of teeth, a rotor, having a rotor core disposed inside the stator and fixed to the rotation shaft and a plurality of permanent magnets attached to the external surface of the rotor core, and a pole-piece unit, having a plurality of first pole pieces and a plurality of second pole pieces arranged radially about the rotation shaft between the stator core and the rotor core such that the plurality of first pole pieces and the plurality of second pole pieces are alternately arranged in a circumferential direction thereof.

Magnetic gear

An emergency power management system of a mobility, may include a fuse device connected to a battery and including a first circuit and a second circuit in which a first fuse and a second fuse are respectively provided and are connected in parallel, a pyro switch provided between the first circuit and the second circuit, and configured to establish electric connection with the first circuit in ordinary times and to release electric connection with the first circuit and to establish electric connection with the second circuit in a case of emergency, a determiner configured to determine abnormality of the first fuse based on current applied from the high-voltage battery or voltages at opposite end portions of the first fuse, and a controller configured to operate the pyro switch when abnormality occurs in the first fuse.

Emergency power management system of mobility and control method thereof

An air mobility craft is provided. The air mobility craft includes a fuselage that has a boarding space and a boarding gate and a plurality of wings disposed on the fuselage. A plurality of rotors are disposed on the wings. A first number of the plurality of rotors are tilting rotors configured to tilt upward or downward for lifting or cruising of the fuselage and a remaining number of the rotors are lifting rotors.

Vertical takeoff and landing air mobility

An apparatus for generating thrust for air transport includes a main thrust device, and an auxiliary thrust device configured to generate auxiliary thrust so as to enable an aircraft to vertically take off and land. The apparatus further includes: wings fixed to left and right sides of a fuselage of the aircraft, rotors installed on the wings and configured to generate thrust. In particular, the main thrust device provides driving force to the rotors using motors and an engine, and the auxiliary thrust device is installed in the fuselage and has a center of gravity configured to coincide with a center of gravity of the aircraft.

Growing community of inventors

Seoul, South Korea

Hyun Woo Jun