Abstract: The invention relates to an electric drive for an aircraft hybrid system. This electric drive comprises a rotor and a stator, wherein the stator may be connected to a structure of the aircraft and the rotor has an annular flange with a shaft through opening for mounting on a propeller flange, wherein the flange is formed of at least two parts, wherein each of these parts of the flange delimits a section of the shaft through opening.

Abstract: According to the invention, a drive device for an aircraft is provided, which has a shaft turbine coupled to an impeller via a shaft. The impeller has an intake side and a thrust side. The shaft turbine is mounted in the area of the intake side of the impeller. The drive device is also designed for mounting externally on an aircraft fuselage and/or inside an aircraft fuselage and/or in a casing on a wing.

Abstract: An internal combustion engine according to the invention comprises at least two engine blocks which are coupled to one another and each of which includes at least two cylinders, each cylinder being connected to a common drive shaft via a transmission and a clutch. If there is a problem with one engine block, same can be disconnected from the drive shaft so that the engine can continue to operate by means of the other engine block.

Abstract: According to the invention, a drive device for an aircraft is provided, which has a shaft turbine coupled to an impeller via a shaft. The impeller has an intake side and a thrust side. The shaft turbine is mounted in the area of the intake side of the impeller. The drive device is also designed for mounting externally on an aircraft fuselage and/or inside an aircraft fuselage and/or in a casing on a wing.

Abstract: An internal combustion engine according to the invention comprises at least two engine blocks which are coupled to one another and each of which includes at least two cylinders, each cylinder being connected to a common drive shaft via a transmission and a clutch. If there is a problem with one engine block, same can be disconnected from the drive shaft so that the engine can continue to operate by means of the other engine block.

Abstract: The lightweight structure according to the invention has at least one substantially plate-shaped structural wall and an enveloping element. The structural wall and the enveloping element are each made of a fibrous composite material. The structural wall is formed from a first fiber outer layer, an intermediate layer and a second fiber outer layer. At least in a sub-region of the end face of the structural wall, a U-shaped profiled connection section (connection section) having a base wall and two side walls is provided. The base wall is arranged to rest against the end face of the structural wall, and the side walls of the U-shaped profiled connection section are arranged to rest against the outer surfaces of the first and second fiber outer layers and are joined to the fiber outer layers.