A power supply device includes a power generator, a drive source, a plurality of power supply lines, a plurality of batteries, a difference calculating unit 11, a difference summing unit 12, and an electric power summing unit 13. The difference calculating unit 11 is configured to calculate differences D1, D2, D3, and D4 between a target charge state set for each battery and an estimated charge state. The difference summing unit 12 is configured to sum the differences D1, D2, D3, and D4 calculated by the difference calculating unit 11. The electric power summing unit 13 is configured to sum the charge state calculated by the difference summing unit 12 and electric power used for the electric loads. A control unit 9 controls the drive source such that electric power calculated by the electric power summing unit 13 is generated by the power generator.

A power supply device includes a power generator, a drive source, a plurality of power supply lines, a plurality of batteries, a current value calculation part 11, a demanded battery power calculation part 12, and a power summation part 13. The current value calculation part 11 calculates the C-rates CR1, CR2, CR3 and CR4 of the batteries based on the charge levels of the batteries. The demanded battery power calculation part 12 calculates a demanded power P or Q of the batteries based on the calculated C-rates CR1, CR2, CR3 and CR4 and the capacities of the batteries. The power summation part 13 sums the demanded power P or Q of the batteries and power demanded by electrical loads. The control unit 9 controls the drive source such that the power generator generates power calculated by the power summation part 13.

A power supply device includes a power generator, a drive source, a plurality of power supply lines, a plurality of batteries, a current value calculation part 11, a demanded battery power calculation part 12, and a power summation part 13. The current value calculation part 11 calculates the C-rates CR1, CR2, CR3 and CR4 of the batteries based on the charge levels of the batteries. The demanded battery power calculation part 12 calculates a demanded power P or Q of the batteries based on the calculated C-rates CR1, CR2, CR3 and CR4 and the capacities of the batteries. The power summation part 13 sums the demanded power P or Q of the batteries and power demanded by electrical loads. The control unit 9 controls the drive source such that the power generator generates power calculated by the power summation part 13.

A rotor system for a rotorcraft includes a first rotor assembly defining a rotation axis, a second rotor assembly offset from the first rotor assembly along the rotation axis, and a drive system connected to the first and second rotor assemblies. The drive system includes a first electric motor disposed along the rotation axis and operably connected to the first rotor assembly, and a second electric motor disposed along the rotation axis and operably connected to the second rotor assembly to rotate the second rotor assembly about the rotation axis independent of rotation of the first rotor assembly about the rotation axis.

An electric propulsion and lift system for an aircraft that includes a plurality of electric motor/propeller assemblies on the flaps of the aircraft so that when the flaps are deflected for take-off and landings, the propellers are directed downward to provide thrust for power lift and increased airflow over the wing for aerodynamic lift. The motor/propeller assemblies are spaced apart and positioned along the entire length of the flaps to provide a distributed airflow.

A converter for an aircraft includes an intermediate circuit for providing a DC voltage between a positive line and a negative line, at least two rectifiers connected to the intermediate circuit to produce the DC voltage from input AC voltages and at least two inverters connected to the intermediate circuit to produce AC output voltages from the DC voltage. The DC voltage terminals of the rectifiers are connected to a first series circuit and the DC voltage terminals of the inverters are connected to a second series circuit. The positive line and the negative line of the intermediate circuit are connected on an input side via the first series circuit and on the output side via the second series circuit. At least one of the DC voltage terminals includes a short circuit for short-circuiting terminal contacts by which the DC voltage terminal is connected to the respective series circuit.

A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.

A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.

Embodiments of a propulsion system are provided herein. In some embodiments, a propulsion system for an aircraft may include an electrical power supply; a motor coupled to the electrical power supply, wherein the electrical power supply provides power to the motor; and a fan disposed proximate a rear portion of an aircraft and rotatably coupled to the motor, wherein the fan is driven by the motor.

The invention relates to a method for providing predefined desired drive characteristics (38, 50) in an aircraft, characterized by the following steps: driving a thrust generation element of the aircraft by means of an electric motor that has actual drive characteristics (34) which include at least some of the desired drive characteristics (38, 50) but are also partly different therefrom; andhaving a control device adjust operating points of the electric motor exclusively according to the desired drive characteristics (38, 50).