Abstract: The disclosure relates to an active part for an electrical machine, wherein the active part includes: a plurality of teeth and a plurality of coils, wherein a coil of the plurality of coils is arranged on each of the teeth, wherein each of the coils has a plurality of prefabricated push-on elements arranged adjacent to one another on the tooth and enclose the tooth in parts, and wherein each of the coils has a plurality of prefabricated connecting elements each for electrically connecting two adjacent push-on elements.

Abstract: An electric motor equipped with a transmission unit in the form of a planetary gear transmission is provided. The planetary gear transmission has a sun gear, planetary gears, and a ring gear, which are coupled to one another via corresponding toothings. The sun gear is coupled directly to a shaft of the electric motor and is fastened thereto. The planetary gears or axles thereof are retained on a bearing plate of the electric motor. The ring gear is rotatably mounted on the housing of the electric motor or is fastened to the housing of the electric motor. A common feature is that parts of the transmission are retained on the housing of the electric motor and not on a separate housing or another component of the transmission unit.

Abstract: The invention relates to an electric motor equipped with a transmission unit, for example in the form of a planetary gear transmission. The planetary gear transmission has a sun gear, a plurality of planetary gears, and a ring gear, which are coupled to one another via corresponding toothings The sun gear is coupled directly to a shaft of the electric motor and is fastened thereto. The planetary gears or the axles thereof are retained on a bearing plate of the electric motor, such that the transmission unit does not have to provide any additional components for this purpose. In one embodiment of the planetary gear transmission, the ring gear is rotatably mounted on the housing of the electric motor. In an alternative embodiment, the ring gear is fastened to the housing of the electric motor.

Abstract: The invention relates to a method for driving an air vehicle using a multilevel converter with at least two converter modules. A first operating voltage is applied to at least one of the converter modules in a first operating state, and a second operating voltage which is lower than the first operating voltage is applied to the converter module in a second operating state. The air vehicle is designed to carry out such a method and comprises an electric drive which has at least one multilevel converter with at least two converter modules, each of which is designed and connected so as to be supplied with a first operating voltage in a first operating state and with a second operating voltage which is lower than the first operating voltage in a second operating state. Advantageously, the air vehicle is an airplane, in particular a hybrid electric airplane.

Abstract: The disclosure relates to a drive system and to a method for providing kinetic energy for a propulsion device of an aircraft. The drive system is designed as a series hybrid system, which has an electric motor for driving the propulsion device, a generator for providing the electrical energy for the electric motor, and an internal combustion engine for providing the kinetic energy for operating the generator. The generator is designed as a superconducting generator. Hydrogen is used as a coolant for the generator. As soon as the hydrogen in the region surrounding the generator exceeds a specified temperature, the hydrogen is drawn from the generator in the gaseous state and fed to a device, which processes the hydrogen in such a way that energy that may be used in the drive system is provided. The device may be a fuel cell and/or the internal combustion engine designed as a hydrogen turbine, for example.

Abstract: 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; and—having a control device adjust operating points of the electric motor exclusively according to the desired drive characteristics (38, 50).

Abstract: The invention relates to a hybrid aircraft (F). According to the invention, a suitable position for mounting an energy generation unit (14) in the aircraft is identified, said energy generation unit comprising an internal combustion engine (34) and an electric generator (30) that is coupled thereto via a shaft. Independently of the position of the energy generation unit (14), a position is also identified for a thrust generation unit (12) comprising an electric motor (24) and a propeller (20) that is coupled thereto via a shaft (22). When the aircraft (F) is built, the thrust generation unit (12) and the energy generation unit (14) are disposed in the positions identified therefor. The generator (30) is then coupled to the electric motor (24) via an electric transmission device (16).

Abstract: 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; and—having a control device adjust operating points of the electric motor exclusively according to the desired drive characteristics (38, 50).

Abstract: A synchrotron radiation source includes a beam guidance system for accelerating and storing an electron or positron particle beam on a closed trajectory. In order to generate the synchrotron radiation, the beam guidance system has at least one approximately achromatic mirror magnet being formed of superconducting winding configurations and in which the trajectory is bent through approximately 270.degree.. Further components of the beam guidance system, such as deflecting magnets and focusing magnets do not necessarily need to be constructed from superconducting components. The synchrotron radiation source permits the utilization of all of the advantages of superconductors with the most extensive avoidance of the disadvantages associated therewith, since the application of superconducting components can be restricted to the components specifically constructed for the generation of the synchrotron radiation.