Abstract: A blade for use in a rotor of an aircraft is swept in a region extending to a blade tip from a first position located between the rotation center of the rotor and the blade tip in a radial direction of the VTOL rotor, the sweep amount increases from the first position toward the blade tip, and the rate of change of the sweep amount in a region extending to the blade tip from a second position located between the first position and the blade tip in the radial direction of the VTOL rotor, is greater than the rate of change of the sweep amount in a region extending from the first position to the second position.

Abstract: In a state where lift is generated in a front wing and a rear wing, a control device for an aircraft controls the pitch of each blade and the stopped state rotation angle of each VTOL rotor to control the force generated in each VTOL rotor in a state where rotation of the VTOL rotor is stopped, thereby applying a force to a fuselage.

Abstract: Four or more rotors installed on an aircraft include: a pair of first rotors that are left/right symmetrically arranged in front of a front wing about a position overlapping the central axis of a fuselage in plan view; and a pair of second rotors that are left/right symmetrically arranged between the front wing and a rear wing about a position overlapping the central axis of the fuselage in a plan view. The distance between the fuselage and the second rotors in the width direction is longer than the distance between the fuselage and the first rotors in the width direction.

Abstract: An aircraft includes a plurality of takeoff and landing rotors each generating a first airflow below the takeoff and landing rotor, and a cruise rotor generating a second airflow behind the cruise rotor, the plurality of takeoff and landing rotors including a rear rotor disposed behind the cruise rotor. The aircraft further includes an airflow deflection mechanism capable of changing a direction of the second airflow, and a controller for controlling the airflow deflection mechanism to suppress interference between the first airflow generated by the rear rotor and the second airflow.

Abstract: The cross-sectional shape of a support member is an airfoil shape in which a first end portion including a first end is curved and which tapers toward a second end. The support member is arranged such that the tapering direction of the airfoil shape is downward, and the tapering direction of the support member is determined in advance according to the moving direction of a blade passing directly above the support member during rotation of a takeoff and landing rotor.

Abstract: The aircraft includes a fuselage, a front wing and a rear wing provided to extend laterally from the fuselage for generating lift during cruise, a boom extending in a front-back direction supported by these wings to be spaced apart from the fuselage, a VTOL rotor supported on the boom and having one or more blades for generating thrust in a vertical direction during take-off and landing, a cooling system for cooling the VTOL rotor by using a radiator arranged within the boom, and an airflow guide structure provided in a part of the boom for guiding airflow generated by rotation of the blades to the radiator, and having an inlet provided on a side that faces toward a rotational direction of the blades relative to a rotational axis of the VTOL rotor, of a surface of the boom positioned below a plane of rotation of the blades.

Abstract: The aircraft includes a fuselage, a front wing and a rear wing provided to extend laterally from the fuselage for generating lift during cruise, a boom 18 supported by the front wing and the rear wing to be spaced apart from the fuselage, and at least one VTOL rotor that is supported on the boom, and having one or more blades for generating thrust in a vertical direction during take-off and landing, wherein the boom has a shape in a top view in which a barrel forms a curvature in a direction away from the fuselage with respect to a front end and a rear end while extending in a front-back direction, and has a cross section in a front view in which an upper side forms a round curvature, the boom being tapered from an upper side from a lower side, and the lower side is substantially flat.

Abstract: An aircraft includes a plurality of takeoff and landing rotors each generating a first airflow below the takeoff and landing rotor, and a cruise rotor generating a second airflow behind the cruise rotor, the plurality of takeoff and landing rotors including a rear rotor disposed behind the cruise rotor. The aircraft further includes an airflow deflection mechanism capable of changing a direction of the second airflow, and a controller for controlling the airflow deflection mechanism to suppress interference between the first airflow generated by the rear rotor and the second airflow.

Abstract: The cross-sectional shape of a support member is an airfoil shape in which a first end portion including a first end is curved and which tapers toward a second end. The support member is arranged such that the tapering direction of the airfoil shape is downward, and the tapering direction of the support member is determined in advance according to the moving direction of a blade passing directly above the support member during rotation of a takeoff and landing rotor.

Abstract: A device capable of supplying an internal combustion engine 60 with a first fuel F1 of a high octane number fuel, and a second fuel F2 of a low octane number fuel or a raw fuel F0. The device is equipped with a cooling medium circulating path LL configured to perform heat exchange between a cooling medium for cooling the internal combustion engine 60 and a separator 20. The device adjusts a flow rate of the cooling medium in the cooling medium circulating path LL, so that a separator temperature T1 is contained in a predetermined temperature range, according to T1, a raw fuel temperature T2 and a cooling medium temperature T3.

Abstract: A device capable of supplying an internal combustion engine 60 with a first fuel F1 of a high octane number fuel, and a second fuel F2 of a low octane number fuel or a raw fuel F0. The device is equipped with a cooling medium circulating path LL configured to perform heat exchange between a cooling medium for cooling the internal combustion engine 60 and a separator 20. The device adjusts a flow rate of the cooling medium in the cooling medium circulating path LL, so that a separator temperature T1 is contained in a predetermined temperature range, according to T1, a raw fuel temperature T2 and a cooling medium temperature T3.

Abstract: To provide a fuel tank capable of easily mixing mixed fuel with water and separating the mixed fuel. The fuel tank comprises a main tank 2, a water tank 3, a separation tank 4, mixed fuel supply unit 6 for supplying the mixed fuel stored in the main tank 2 to the separation tank 4, water supply unit 11 for supplying water stored in the water tank 3 to the separation tank, gasoline supply unit 14 for supplying gasoline to an engine, and alcohol-water supply unit 16 for supplying an alcohol-water mixed liquid to the engine.