Abstract: A hybrid aircraft that flies by using a plurality of rotors (takeoff and landing rotors and cruise rotors) includes a generator, a battery charged with power generated by the generator, a plurality of electric motors that rotate the respective rotors by the power generated by the generator and power supplied from the battery, and a controller that sets a target remaining capacity of the battery according to a flight state of the aircraft and controls charging and discharging of the battery so that the remaining capacity of the battery approaches the target remaining capacity.

Abstract: A control device includes an acquisition unit configured to acquire information indicating a battery output limit value that is a maximum value of electric power that can be supplied from a battery to an electric load, and a control unit configured to, when electric power supplied from a first battery to a first electric load is expected to exceed a first battery output limit value, execute control of increasing electric power supplied from a battery other than the first battery and reducing electric power supplied from the first battery to the first electric load.

Abstract: An electric power control device includes an acquisition unit configured to acquire information indicating a maximum power value that is a maximum value of electric power that can be output from a battery without causing an excessive output voltage drop and information indicating a requested power value, a determination unit configured to determine a suppliable power value indicating electric power that can be supplied from the battery to a starting mechanism when starting a stopped internal combustion engine, based on a difference between a maximum power value and a requested power value, and a control unit configured to start the internal combustion engine using electric power corresponding to the suppliable power value determined by the determination unit.

Abstract: Before power is supplied to a load from a capacitor and a plurality of batteries, a battery for initially supplying power for charging to the capacitor is determined from among the plurality of batteries, based on a result of acquiring the voltage of each battery, and voltage equalization of the plurality of batteries is performed in response to power for charging being supplied to the capacitor from the determined battery.

Abstract: Provided is a multicopter providing a high level of freedom in compact design, and consuming a relatively small amount of energy. The multicopter (10) includes a machine body (12), an N number of first lift generators (30) arranged on a first concentric circle (C1) centered substantially around a gravitational center (G) of the machine body (12) and in a front part and a rear part of the machine body in a bilateral symmetry, and an M number of second lift generators (70) arranged on a second concentric circle (C2) centered substantially around the gravitational center (G) of the machine body (12) and having a larger diameter than the first concentric circle (C1), and in a front part and a rear part of the machine body (12) on a central axial line (X) extending in a fore and aft direction of the machine body (12), N being greater than M.

Abstract: When a difference in the SOC among respective batteries is greater than or equal to a first prescribed value, an electric motor control section reduces output power of a cruise electric motor that operates using electric power of a battery with a low SOC and increases output power of a cruise electric motor that operates using electric power of a battery with a high SOC.

Abstract: A charging control system (70) includes a power unit having a power generation apparatus (40a) configured to perform power generation to supply electric power to a load, and a battery (32) configured to accumulate the electric power supplied from the power generation apparatus and supply the electric power that is accumulated to the load, and a control section (91) configured to apply a target power feed amount indicating an amount of power to be supplied to the load and a target power charge amount indicating an amount of power to be stored in the battery to a charge loss characteristic of the battery and a fuel consumption characteristic of the power generation apparatus to decide a fuel consumption of the power generation apparatus and to control charge of the battery based on the fuel consumption. In accordance with this, the fuel consumption can be suppressed.

Abstract: A power supply device includes a power generator, a drive source, a plurality of power supply lines, a plurality of batteries, a diode, a difference calculating unit 11, 12, 13, or 14, and a difference summing unit 16. The difference calculating unit 11, 12, 13, or 14 is configured to calculate a difference between demanded electric power P1, P2, P3, or P4 in the corresponding power supply line and a charge state of the corresponding battery. The difference summing unit 16 is configured to sum the differences in electric power in the power supply lines calculated by the difference calculating units 11, 12, 13, and 14. In the power supply device, the drive source is controlled such that electric power equal to or higher than the electric power calculated by the difference summing unit 16 is generated by the power generator.

Abstract: A power unit control system includes: a gas turbine including a turbine rotor; an energy converter being able to operate as a power generator that generates electric power with rotation of the gas turbine; a battery that stores electric power generated by the energy converter; a reception portion that receives a signal which is transmitted from a device controller that controls a device operating using the electric power stored in the battery or electric power generated by the energy converter; and a control portion that performs rotation speed increase control which increases the rotation speed of the gas turbine to a predetermined rotation speed when a predetermined first signal is received by the reception portion.

Abstract: An aircraft propulsion system capable of improving the restartability of an engine is provided. An aircraft propulsion system includes: a plurality of engines (60-1 and 60-2); an electric generator connected to engine shafts (63-1 and 63-2); a plurality of electric motors; a plurality of rotors; and a controller (100) which controls an operation state of the plurality of engines (60-1 and 60-2). The controller (100) causes a part of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine when a flight state is in a first state. The plurality of engines (60-1 and 60-2) include circulators (65-1 and 65-2). A plurality of communication pipes (68 and 69) which communicate the circulator (65-1) in the first engine (60-1) among the plurality of engines (60-1 and 60-2) with the circulator (65-2) in the second engine (60-2) are provided.

Abstract: Technology for operating an engine smoothly is provided. In an aircraft propulsion system, a controller causes at least a first engine among the plurality of engines to be stopped and causes a second engine, which has not been stopped, to be operated when an aircraft is flying in a prescribed flight mode and causes the first engine to be operated and causes the second engine to be stopped when a detector detects that the temperature related to the first engine is less than or equal to a first prescribed temperature.

Abstract: A power supply system includes a rotor for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a battery for supplying power to the component group. The rotor includes a VTOL rotor and a cruise rotor, and the component group includes a VTOL component group and a cruise component group. The VTOL component group and the cruise component group are supplied with power from the same battery.

Abstract: A hybrid aircraft that flies by using a plurality of rotors (takeoff and landing rotors and cruise rotors) includes a generator, a battery charged with power generated by the generator, a plurality of electric motors that rotate the respective rotors by the power generated by the generator and power supplied from the battery, and a controller that sets a target remaining capacity of the battery according to a flight state of the aircraft and controls charging and discharging of the battery so that the remaining capacity of the battery approaches the target remaining capacity.

Abstract: Before power is supplied to a load from a capacitor and a plurality of batteries, a battery for initially supplying power for charging to the capacitor is determined from among the plurality of batteries, based on a result of acquiring the voltage of each battery, and voltage equalization of the plurality of batteries is performed in response to power for charging being supplied to the capacitor from the determined battery.

Abstract: Technology for operating an engine smoothly is provided. In an aircraft propulsion system, a controller causes at least a first engine among the plurality of engines to be stopped and causes a second engine, which has not been stopped, to be operated when an aircraft is flying in a prescribed flight mode and causes the first engine to be operated and causes the second engine to be stopped when a detector detects that the temperature related to the first engine is less than or equal to a first prescribed temperature.

Abstract: An aircraft propulsion system capable of improving the restartability of an engine is provided. An aircraft propulsion system includes: a plurality of engines (60-1 and 60-2); an electric generator connected to engine shafts (63-1 and 63-2); a plurality of electric motors; a plurality of rotors; and a controller (100) which controls an operation state of the plurality of engines (60-1 and 60-2). The controller (100) causes a part of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine when a flight state is in a first state. The plurality of engines (60-1 and 60-2) include circulators (65-1 and 65-2). A plurality of communication pipes (68 and 69) which communicate the circulator (65-1) in the first engine (60-1) among the plurality of engines (60-1 and 60-2) with the circulator (65-2) in the second engine (60-2) are provided.

Abstract: An aircraft propulsion system capable of improving power generation efficiency is provided. When a flight state of an aircraft is a first state after a plurality of engines operate and the aircraft takes off, the aircraft propulsion system causes at least one engine among the plurality of engines to be stopped, causes another engine, which has not been stopped, to be operated in an operating range in which the other engine is able to operate efficiently, and causes a generator corresponding to the other engine to output power.

Abstract: An aircraft propulsion system capable of reducing a rotational load of an engine shaft is provided. An aircraft propulsion system includes a plurality of engines (60-1 and 60-2) and a controller (100). When a flight state is a first state, the controller (100) causes some of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine. At least one engine (60-1) of the plurality of engines (60-1 and 60-2) includes a bleed air hole (71-1), a bleed air pipe (72-1), and a bleed air valve (73-1). When causing the engine (60-2) which has stopped to start up again, the controller (100) opens a bleed air valve (73-1) in the engine (60-1) which is in operation and supplies compressed air of the compressor (62-1) to the compression chamber (64-2) of the engine (60-2) which has stopped.

Abstract: Provided is a multicopter providing a high level of freedom in compact design, and consuming a relatively small amount of energy. The multicopter (10) includes a machine body (12), an N number of first lift generators (30) arranged on a first concentric circle (C1) centered substantially around a gravitational center (G) of the machine body (12) and in a front part and a rear part of the machine body in a bilateral symmetry, and an M number of second lift generators (70) arranged on a second concentric circle (C2) centered substantially around the gravitational center (G) of the machine body (12) and having a larger diameter than the first concentric circle (C1), and in a front part and a rear part of the machine body (12) on a central axial line (X) extending in a fore and aft direction of the machine body (12), N being greater than M.

Abstract: An internal combustion engine fuel supply system includes a first fuel tank, a separator, and circuitry. The first fuel tank is to store fuel. The separator is connected to the first fuel tank to separate the fuel supplied from the first fuel tank into a high octane fuel and a low octane fuel which are to be supplied to an internal combustion engine. The high octane fuel has a first octane number. The low octane fuel has a second octane number lower than the first octane number. The circuitry is configured to determine whether fuel has been supplied to the first fuel tank, and to operate the separator to separate the fuel into the high octane fuel and the low octane fuel when it is determined that fuel has been supplied to the first fuel tank.