Closing timing of an intake port is changed without using a variable valve timing mechanism. An electric vehicle includes an engine for electricity generation in which closing timing of an intake port maximizes intake air charging efficiency in a specific revolution speed region, a sensor which outputs a signal related to a revolution speed of the engine, a controller which drives the engine at a revolution speed based on the signal of the sensor, a requested electricity generation amount being satisfied at the revolution speed, and a motor which applies a positive or negative torque to the engine. When the engine is driven in a revolution speed region other than the specific revolution speed region, the controller uses the motor to apply a positive or a negative torque to the engine in an intake stroke to change the closing timing of the intake port to increase intake air charging efficiency.

A battery control device includes: an input unit that selects and inputs a first battery operation mode that is one of a plurality of battery operation modes that control discharging from a battery to an electric motor and charging from a generator to the battery by an operation of an occupant of the vehicle; a selection status display unit that displays a mode indicator corresponding to each of the plurality of battery operation modes and displays a selection status in the input unit; a confirmation unit that confirms the first battery operation mode when a selected state of the first battery operation mode is maintained for a predetermined time after the first battery operation mode is selected in the input unit; and a battery operation control unit that controls the operation of the battery of the vehicle based on the first battery operation mode confirmed by the confirmation unit.

The disclosure relates to a hybrid-electrical drive system for an aircraft having two subsystems that are largely independent of each other. A stator winding of a common electrical machine is assigned to each of the subsystems such that both subsystems may be supplied with electrical energy from the common electrical machine. If a defect occurs in one of the subsystems, the drive system may be configured such that electrical energy from a battery of the non-defective subsystem may be transferred into the defective subsystem by utilizing the two stator winding systems.

Modestly modified automotive engine powered generator systems to substantially improve capability for providing renewable electricity powered grid reliability and energy storage are disclosed. The use of these engines to improve capability for non-grid electricity generation, including affordable and clean fast charging of electric vehicles, is also disclosed. In one embodiment, these automotive engines use high RPM and stoichiometric air fuel ratio operation so as to provide the advantages of substantially reduced cost and NOx emissions. These engines also have multifuel capability that provides highly flexible use of low carbon fuels (such as hydrogen, methanol and ammonia) as well as the use of present fuels that are widely available. When these low-carbon fuels are produced with excess electricity from the grid and supplied to the grid when there is an electricity-supply shortfalls, they can serve as a means of energy storage.

Modestly modified automotive engine powered generator systems to substantially improve capability for providing renewable electricity powered grid reliability and energy storage are disclosed. The use of these engines to improve capability for non-grid electricity generation, including affordable and clean fast charging of electric vehicles, is also disclosed. In one embodiment, these automotive engines use high RPM and stoichiometric air fuel ratio operation so as to provide the advantages of substantially reduced cost and NOx emissions. These engines also have multifuel capability that provides highly flexible use of low carbon fuels (such as hydrogen, methanol and ammonia) as well as the use of present fuels that are widely available. When these low-carbon fuels are produced with excess electricity from the grid and supplied to the grid when there is an electricity-supply shortfalls, they can serve as a means of energy storage.

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 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 control circuit for a dual fuel generator includes a primary fuel valve to control the supply of a primary fuel, a secondary fuel valve to control the supply of a secondary fuel, a primary fuel pressure switch to detect the primary fuel, a secondary fuel pressure switch to detect the secondary fuel, and a controller. The controller is configured to receive a primary signal for availability of the primary fuel from the primary fuel pressure switch and a secondary signal for availability of the secondary fuel from the secondary and operate the primary fuel valve and the secondary fuel valve in response to the primary signal and the secondary signal. When the secondary fuel valve is open so that the secondary fuel is provided to the dual fuel generator, the control circuit is configured to ground the primary signal by connecting the primary fuel pressure switch to ground.