A power distribution system 100 is installed in an aircraft, and comprises: a first DC power supply unit 10 including a generator 11; a second DC power source unit 20 including a battery 30, a step-up/down converter 41, a voltage sensor 43, and control unit 44; and a diode 50. When the voltage sensor 43 does not detect regenerative power, the control unit 44 executes a running power processing mode in which generated power generated by the first DC power supply unit 10 is supplied to an electric actuator 80 while charging and discharging the battery 30 using the step-up/down converter 41 so as to keep a charge rate A of the battery 30 within a predetermined range. When the voltage sensor 43 detects regenerative power, the control unit 44 executes a regenerative power processing mode in which the battery 30 is charged with the regenerative power using the step-up/down converter 41.

A first propeller has a shorter blade length and a lower inertia than a second propeller. An electromagnetic field emitter is coupled to one of the first propeller or the second propeller and an electromagnetic field receptor is coupled to the other one that is not coupled to the electromagnetic field emitter. The electromagnetic field emitter emits an electromagnetic field. In response to the electromagnetic field: the electromagnetic field receptor and its coupled propeller rotate in a first rotational direction; and the electromagnetic field emitter and its coupled propeller rotate in a second and counter-rotational direction. In response to a second electromagnetic field associated with increasing torque: the first propeller increases and subsequently decreases its rotational speed; and the second propeller increases its rotational speed at a slower rate than the increase in the rotational speed of the first propeller.

A first propeller has a shorter blade length and a lower inertia than a second propeller. An electromagnetic field emitter is coupled to one of the first propeller or the second propeller and an electromagnetic field receptor is coupled to the other one that is not coupled to the electromagnetic field emitter. The electromagnetic field emitter emits an electromagnetic field. In response to the electromagnetic field: the electromagnetic field receptor and its coupled propeller rotate in a first rotational direction; and the electromagnetic field emitter and its coupled propeller rotate in a second and counter-rotational direction. In response to a second electromagnetic field associated with increasing torque: the first propeller increases and subsequently decreases its rotational speed; and the second propeller increases its rotational speed at a slower rate than the increase in the rotational speed of the first propeller.

A configuration instruction associated with configuring a plurality of batteries which supply power to a plurality of motors in a vehicle is received. The batteries are configuring as specified by the configuration instruction, where the batteries are able to be configured in a plurality of configurations, including: a first configuration where at least some of the batteries are electrically connected together in parallel and a second configuration where at least some of the batteries are electrically connected together in series.

A configuration instruction associated with configuring a plurality of batteries which supply power to a plurality of motors in a vehicle is received. The batteries are configuring as specified by the configuration instruction, where the batteries are able to be configured in a plurality of configurations, including: a first configuration where at least some of the batteries are electrically connected together in parallel and a second configuration where at least some of the batteries are electrically connected together in series.

A vehicle includes a tilt rotor that is aft of a fixed wing and that is attached to the fixed wing via a pylon. A flight computer configured to instruct the tilt rotor to produce a maximum downward angle including by updating an actuator authority database associated with the flight computer to reflect the maximum downward angle, and generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the maximum downward angle, wherein the maximum downward angle is adjustable.

A vehicle includes a tilt rotor that is aft of a fixed wing and that is attached to the fixed wing via a pylon. A flight computer configured to instruct the tilt rotor to produce a maximum downward angle including by updating an actuator authority database associated with the flight computer to reflect the maximum downward angle, and generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the maximum downward angle, wherein the maximum downward angle is adjustable.

A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or fan drive motor. Electrical power is provided to the drive motor by a high efficiency electrical power generator with reduced electromagnetic drag or reverse torque. The electric generator utilizes a solid state rotor that does not rotate which allows for power generation without reverse torque or the usual energy required to rotate the rotor inside the stator of the generator. Only the magnetic poles of the disclosed rotor rotate to generate the power. The fan blades of the turbofan jet engine are driven by the electric drive motor in which the rotor is a part of the fan as well as the drive from the high pressure turbine.

A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or fan drive motor. Electrical power is provided to the drive motor by a high efficiency electrical power generator with reduced electromagnetic drag or reverse torque. The electric generator utilizes a solid state rotor that does not rotate which allows for power generation without reverse torque or the usual energy required to rotate the rotor inside the stator of the generator. Only the magnetic poles of the disclosed rotor rotate to generate the power. The fan blades of the turbofan jet engine are driven by the electric drive motor in which the rotor is a part of the fan as well as the drive from the high pressure turbine.

Heating a battery and cooling an electric power conversion device are achieved together. This mobile body includes an electric motor, a battery, a thermoelectric conversion element, an electric power conversion device, and a controller. The electric motor is a driving source. The electric power conversion device is configured to convert electric power outputted from the battery into driving electric power for the electric motor. The electric power conversion device is disposed in direct contact or in indirect contact with the battery with the thermoelectric conversion element interposed therebetween. The controller is configured to control electric power to be supplied to the thermoelectric conversion element. The controller controls, in a case where the battery is in a predetermined low-temperature state, the electric power to be supplied to the thermoelectric conversion element to cause a surface of the thermoelectric conversion element coupled to the battery to serve as a heat dissipation surface.