Electric drive device for an aircraft

An aircraft comprising:

• a drive device comprising at least a battery for storage of electrical energy, an electric motor for the propulsion of a propeller , a conductive means for transferring the electrical energy from the battery to the electric motor, and a first control means for controlling the electric motor, wherein
• the battery is a lithium-air battery, the electric motor is a high-temperature superconductor motor, that at least one reservoir for a coolant and a cooling system connected with the reservoir for cooling the high-temperature superconductor motor is provided, wherein the cooling system comprises a second control means for controlling the cooling system,
• a first means for the variable configuration of the lithium-air battery and/or a second means for the variable configuration of the reservoir in the aircraft is/are provided, and
• a third control means for controlling the first and/or the second means is provided, wherein the control of the first and/or the second means occurs such that the lithium air-battery and/or the reservoir in the aircraft are configured such that a mass increase of the lithium-air battery which results during an operation of the drive device and a mass decrease of the liquid nitrogen in the reservoir that results during an operation of the drive device will not change a center of gravity position of the aircraft.