The propulsion system have a load change detecting unit detecting a load change and an operating point control unit controlling power operating points defined using a torque T and a rotation number Ne. The operating point control unit calculates target power operating points 44 and 54 corresponding to the load after change for first power operating points 41 and 51 that are current power operating points in a case in which a change in the load is detected by the load change detecting unit. By changing the fuel flow in a range not exceeding a predetermined fuel line, the operating point control unit moves the power operating points from first power operating points 41 and 51 to second power operating points 42 and 52, third power operating points 43 and 53, and target power operating points 44 and 54 in order.

A multicopter comprises: a support; rotors supported by the support; an internal combustion engine supported by the support; a generator supported by the support and driven by the internal combustion engine to generate power; electric motors supported by the support, supplied with electric power from the generators, and configured to drive the rotors; and a circuitry that control a flight of an aircraft by individually adjusting a rotational speed of each of the rotors. The multicopter also comprises a plurality of the internal combustion engines or a plurality of the generators.

A multicopter is provided with: a support; multiple rotors provided to the support; an engine which is provided to the support and capable of varying the output thereof; an electric generator which is supported by the support and generates electricity by being driven by the engine; a capacitor which is provided to the support; multiple motors which are provided to the support, which are configured to be capable of supplying electricity from the electric generator and the capacitor, and which drive the multiple rotors respectively; a flight controller which controls the attitude of the multicopter main body by adjusting the revolving speeds of the respective rotors; and a power plant controller which controls the electric power to be generated by controlling both the engine and the electric generator in accordance with a control instruction given by the flight controller.

A multicopter is provided with: a support; multiple rotors provided to the support; an engine which is provided to the support and capable of varying the output thereof; an electric generator which is supported by the support and generates electricity by being driven by the engine; a capacitor which is provided to the support; multiple motors which are provided to the support, which are configured to be capable of supplying electricity from the electric generator and the capacitor, and which drive the multiple rotors respectively; a flight controller which controls the attitude of the multicopter main body by adjusting the revolving speeds of the respective rotors; and a power plant controller which controls the electric power to be generated by controlling both the engine and the electric generator in accordance with a control instruction given by the flight controller.

A method of operating a multi-engine system of an aircraft having first and second engines includes accumulating compressed air in a pressure vessel external to the engines, and operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine. In response to a power demand request, the second engine is accelerated out of the standby operating condition by introducing therein compressed air from the pressure vessel at a location upstream of a combustor of the second engine.

A method of operating a multi-engine system of an aircraft having first and second engines includes accumulating compressed air in a pressure vessel external to the engines, and operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine. In response to a power demand request, the second engine is accelerated out of the standby operating condition by introducing therein compressed air from the pressure vessel at a location upstream of a combustor of the second engine.

To provide a flying object capable of suppressing ignition of a secondary battery due to overcharging. A flying object includes a fuel cell, a secondary battery, a motor, an air resistance increasing device capable of increasing the air resistance, and a control unit. The motor drives a propulsion propeller. The fuel cell, the secondary battery, and the motor are electrically connected. The motor is driven by obtaining power from at least one of the fuel cell and the secondary battery. When the fuel cell generates an amount of power exceeding a power consumption amount, the control unit increases an amount of power supplied to the motor from the fuel cell while increasing the air resistance by operating the air resistance increasing device, and performs a power consumption control to maintain a flight state.

To provide a flying object capable of suppressing ignition of a secondary battery due to overcharging. A flying object includes a fuel cell, a secondary battery, a motor, an air resistance increasing device capable of increasing the air resistance, and a control unit. The motor drives a propulsion propeller. The fuel cell, the secondary battery, and the motor are electrically connected. The motor is driven by obtaining power from at least one of the fuel cell and the secondary battery. When the fuel cell generates an amount of power exceeding a power consumption amount, the control unit increases an amount of power supplied to the motor from the fuel cell while increasing the air resistance by operating the air resistance increasing device, and performs a power consumption control to maintain a flight state.

A system includes a starter generator configured to provide power to a first bus and a first inverter, a second inverter coupled to the first inverter, a first switch configured to selectively couple the second inverter to the first bus and to a second bus, a second switch configured to selectively couple a first motor to the first bus and to the second bus, and a controller. The controller sets the first switch to a second position and the second switch to a second position, causes the second inverter to convert the power from the first inverter to a starting power for starting the first motor, causes the second inverter to increase the starting power to match the power provided to the first bus from the starter generator, and switches the second switch to the first position, when the starting power matches the power from the starter generator.

A system includes a starter generator configured to provide power to a first bus and a first inverter, a second inverter coupled to the first inverter, a first switch configured to selectively couple the second inverter to the first bus and to a second bus, a second switch configured to selectively couple a first motor to the first bus and to the second bus, and a controller. The controller sets the first switch to a second position and the second switch to a second position, causes the second inverter to convert the power from the first inverter to a starting power for starting the first motor, causes the second inverter to increase the starting power to match the power provided to the first bus from the starter generator, and switches the second switch to the first position, when the starting power matches the power from the starter generator.