Abstract: The present disclosure relates to a fuel cell system and an aircraft equipped with a fuel cell system. The aircraft may have a fuselage elongated in a front-rear direction, a front horizontal stabilizer towards a front of the fuselage, main wings extending to opposite sides of the fuselage, a rear horizontal stabilizer towards a rear of the fuselage, the fuel cell system rear to the main wings and a controller. The fuel cell system may be configured to provide electrical energy for driving a motor on each of the main wings. The controller may be configured to cause transmission of electrical energy from the fuel cell system to the motor. A center of gravity of the aircraft may be near front edges of the main wings. A flow rate of air into the fuel cell system may be controlled in response to an outside air condition.

Abstract: An aircraft includes a fuselage extending in a front-rear direction of the aircraft, main wings extending from sides of the fuselage, a fuel cell system located adjacent to a rear of the fuselage with respect to the main wings and configured to apply driving force to a nacelle located on each of the main wings, and a controller configured to transmit electrical energy applied from the fuel cell system to the nacelle. A center of gravity of the aircraft is located in the fuselage close to front ends of the main wings, and a flow rate of air flowing into the fuel cell system is controlled in response to an outside air condition of the aircraft.

Abstract: A hybrid air mobility system is capable of flying a long distance through effective operation of an engine and batteries. The hybrid air mobility system includes a fuselage configured to supply power to a propeller and electric equipment, the fuselage being provided with a duct including an inlet and an outlet so as to circulate air to the engine and the electric equipment; a deflector rotatably installed at the outlet of the duct so as to convert a discharge direction of exhaust gas generated by the engine and cooling air after cooling the electric equipment; and a controller configured to determine whether or not the engine is driven and to control a rotated position of the deflector depending on an amount of driving of the engine so as to selectively adjust movement of the exhaust gas and the cooling air towards the propeller.

Abstract: A hybrid air mobility system is capable of flying a long distance through effective operation of an engine and batteries. The hybrid air mobility system includes a fuselage configured to supply power to a propeller and electric equipment, the fuselage being provided with a duct including an inlet and an outlet so as to circulate air to the engine and the electric equipment; a deflector rotatably installed at the outlet of the duct so as to convert a discharge direction of exhaust gas generated by the engine and cooling air after cooling the electric equipment; and a controller configured to determine whether or not the engine is driven and to control a rotated position of the deflector depending on an amount of driving of the engine so as to selectively adjust movement of the exhaust gas and the cooling air towards the propeller.