An aircraft power control device for controlling electric power in an aircraft includes a DC/DC-converter configured for receiving a DC input voltage on a converter input side, converting the received DC input voltage into a DC output voltage and outputting the DC output voltage on a converter output side and an electric power switch is electrically coupled to the converter output side of the DC/DC-converter. The electric power switch is switchable between a switched-on state and a switched-off state. The switch output side is electrically coupled with the switch input side of the electric power switch when in the switched-on state, and wherein the switch output side is electrically isolated from the switch input side of the electric power switch, when in the switched-off state. The system also includes a monitoring device to control the state of the switch.

A power distribution system includes a plurality of energy supply systems, a plurality of first electric propulsion units, and a second electric propulsion unit different from the plurality of first electric propulsion units. Each energy supply system is configured to power at least two of the first electric propulsion units and each first electric propulsion unit is configured to be powered by at least two of the energy supply systems. Further, at least a subset of the energy supply systems is configured to power the second electric propulsion unit.

Various aspects of the techniques are directed to a turbine engine comprising a core section, a fan, and an electrical generator. The core section includes a low pressure turbine that drives a low pressure spool that rotates about a longitudinal axis of the turbine engine, a high pressure turbine that drives a high pressure spool, and a compressor rotated by the high pressure spool. The fan is connected to the low pressure spool and rotated by the low pressure spool. Rotation of the fan may provide thrust to a vehicle that includes the turbine engine. The electrical generator is positioned between the fan and the compressor. The electrical generator comprises a rotor concentric with and rotated via the low pressure spool, the rotor configured to rotate about the longitudinal axis, and a stator positioned radially within the rotor and configured to electromagnetically interact with the rotor to generate power.

Various aspects of the techniques are directed to a turbine engine comprising a core section, a fan, and an electrical generator. The core section includes a low pressure turbine that drives a low pressure spool that rotates about a longitudinal axis of the turbine engine, a high pressure turbine that drives a high pressure spool, and a compressor rotated by the high pressure spool. The fan is connected to the low pressure spool and rotated by the low pressure spool. Rotation of the fan may provide thrust to a vehicle that includes the turbine engine. The electrical generator is positioned between the fan and the compressor. The electrical generator comprises a rotor concentric with and rotated via the low pressure spool, the rotor configured to rotate about the longitudinal axis, and a stator positioned radially within the rotor and configured to electromagnetically interact with the rotor to generate power.

The earth's magnetic field has not been mined as a source of energy. With average field strength of 0.510.sup.4 Tesla around the world it is easy to understand why. A disruptive technology is needed to mine the earth's magnetic field. Such a technology, graphene, is now at an early stage of development with excellent properties in the form of high conductivity, low resistivity, durable, light weight, low cost sheets. Multiple sheets of graphene provide a significant multiplier to earth's magnetic field yielding a feasible source of ecologically clean power. Graphene based EcoCharge units can be driven by electric motors putting graphene in motion to mine the earth's magnetic field. Estimates show that for a Solar Impulse 2 like electric plane, eight EcoCharge units weighing 64 lbs generate 60 kW RMS continuously replacing 3,000 lbs of photovoltaic cells generating 50 kW RMS during the day only.

An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.

An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.

A power converter for use with a fan engine of an aircraft comprises an electric-motor interface for electrical connection to an electric motor configured to be mechanically coupled to a driveshaft of the fan engine. The converter includes an inverting electric-motor power stage, having a DC side and an AC side, wherein the AC side of the electric-motor power stage is electrically coupled to the electric-motor interface. It comprises a thrust-reverser interface for electrical connection to an electric actuator of the fan engine for actuating a thrust reverser surface of the fan engine, and an inverting thrust-reverser power stage, having a DC side and an AC side, wherein the AC side of the thrust-reverser power stage is electrically coupled to the thrust-reverser interface.

A power converter for use with a fan engine of an aircraft comprises an electric-motor interface for electrical connection to an electric motor configured to be mechanically coupled to a driveshaft of the fan engine. The converter includes an inverting electric-motor power stage, having a DC side and an AC side, wherein the AC side of the electric-motor power stage is electrically coupled to the electric-motor interface. It comprises a thrust-reverser interface for electrical connection to an electric actuator of the fan engine for actuating a thrust reverser surface of the fan engine, and an inverting thrust-reverser power stage, having a DC side and an AC side, wherein the AC side of the thrust-reverser power stage is electrically coupled to the thrust-reverser interface.

An aircraft includes: a gas turbine for driving a generator; a first electric motor for driving a first rotor; and a second electric motor for driving a second rotor. The gas turbine is arranged in a manner so that the gas turbine overlaps a rear wing in the front-rear direction of a fuselage, and a first high-voltage harness for transmitting electric power to the first electric motor and a second high-voltage harness for transmitting electric power to the second electric motor are arranged inside the rear wing so as to be separated from each other in the front-rear direction of the fuselage.