Abstract: A gas mixing device for a moving object including a discharge flow path that discharges an exhaust gas from a gas turbine engine. The discharge flow path includes a tubular portion, a communication passage that allows an inside of the tubular portion and the gas turbine engine to communicate with each other, and a plurality of guide portions that extend radially inward from the tubular portion and guide the cooling gas to a radially central portion of the tubular portion. The plurality of guide portions are spaced from each other in a circumferential direction of the tubular portion, and the extended end portions of the plurality of guide portions are spaced from each other.

Abstract: The aircraft includes a fuselage, an engine disposed in the fuselage, an exhaust outlet provided at a tail of the fuselage for discharging exhaust gas from the engine to the outside, and a cruise rotor positioned rearward of the exhaust outlet and generating horizontal thrust on the fuselage. The exhaust outlet and the cruise rotor do not overlap each other when viewed from the direction in which the exhaust gas is discharged.

Abstract: An aircraft including a fuselage with a cooling unit including a first radiator, a second radiator, a first cooling fan and a second cooling fan for taking air outside the fuselage into the fuselage and supplying air to the first radiator and the second radiator. The aircraft has an exhaust orifice for discharging air delivered into the interior of the fuselage, the cooling unit is arranged forward of the engine in the fuselage, and the exhaust orifice is positioned rearward of the engine in the fuselage.

Abstract: A gas mixing device for a moving object including a discharge flow path that discharges an exhaust gas from a gas turbine engine. The discharge flow path includes a tubular portion, a communication passage that allows an inside of the tubular portion and the gas turbine engine to communicate with each other, and a plurality of guide portions that extend radially inward from the tubular portion and guide the cooling gas to a radially central portion of the tubular portion. The plurality of guide portions are spaced from each other in a circumferential direction of the tubular portion, and the extended end portions of the plurality of guide portions are spaced from each other.

Abstract: A moving object includes equipment disposed in a first area and including an engine and a power generator driven by the engine, equipment disposed in a second area located forward of the first area in a traveling direction of the moving object and including an electric power device supplying electric power from the power generator to a battery, and equipment disposed in a third area located forward of the second area in the traveling direction and including the battery.

Abstract: A cooling system includes: an acquisition unit that acquires information about the rotational speed of a rotating electric machine and information about the torque of the rotating electric machine; a cooling device that cools a cooling target; and a control unit that controls the cooling device based on a feedforward value generated based on the rotational speed and the torque.

Abstract: An aircraft cooling system includes: a rotor capable of generating thrust in a vertical direction; a heat generating member disposed below the rotor; a support member (a boom) that supports the heat generating member; a structure (a second fairing) protruding from the support member toward the rotor; and a heat exchanger (a surface heat exchanger) provided in the structure. A refrigerant heated by the heat generating member is introduced to an inlet (a fairing inlet) provided in the heat exchanger, and the refrigerant cooled by the heat exchanger is supplied to the heat generating member from an outlet (a fairing outlet) provided in the heat exchanger.

Abstract: An electric power system of a moving object includes a gas turbine engine including a compressor and a rotating electric machine connected to the gas turbine engine, a first bleed air flow path configured to introduce bleed air obtained by taking out a part of air compressed by the compressor into the rotating electric machine, and a second bleed air flow path configured to guide the bleed air introduced into the rotating electric machine to a component requiring cooling of the turbine engine.

Abstract: A VTOL aircraft (moving object) includes: a first communication path allowing a cabin (passenger compartment) and a component compartment to communicate with each other; and a second communication path for opening the component compartment to the outside of a fuselage. A portion of air in the cabin flows through a first circulation path and returns to the cabin, and the remaining air in the cabin flows through the first communication path and is introduced into the component compartment. A portion of air in the component compartment flows through a second circulation path and returns to the component compartment, and the remaining air in the component compartment flows through the second communication path and is discharged to the outside of the fuselage.