ELECTRIC DRIVE DEVICE FOR AN AIRCRAFT

摘要

The invention relates to a drive device for an aircraft (100), at least comprising a battery (101) for storing electrical energy, an electric motor (103) for driving a propeller (104), a conducting means (102) for transferring the electrical energy from the battery (101) to the electric motor (103), and a first control means (201) for controlling said electric motor (103). The invention is characterised in that: the battery (101) is a lithium-air battery; the electric motor (103) is a high-temperature superconductor motor; at least one store (105) is provided for a coolant and a cooling system which is connected to said store (105) for cooling said high-temperature superconductor motor (103), the cooling system comprising a second control means (202) for controlling said cooling system; a first means (204) is provided for variably arranging the lithium-air battery (101) and/or a second means (205) is provided for variably arranging the store (105) in the aircraft (100); and a third control means (203) is provided for controlling the first (204) and/or the second (205) means.

主权项

1. A drive device for an aircraft, 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.