Electric drive for an aircraft and hybrid system for an aircraft
OwnerJohann Schwöllerinventor
Life of this patent
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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.
Claims18
An electric drive for an aircraft hybrid system comprising a rotor, a stator, wherein the stator connects 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 one end face of the annular flange is described as a propeller side and another end face as a motor side, wherein a bearing housing section is formed on the motor side and a rotor bearing section is formed on the propeller side, and the stator has an annular bearing device and a torque support, wherein the bearing device is provided in the area of the bearing housing section of the annular flange and the rotor is fixed on the rotor bearing section of the annular flange, wherein reaction torque of the stator is delivered via the torque support to the structure of the aircraft, where the reaction torque is absorbed.
An electric drive for an aircraft hybrid system of an aircraft, the electric drive comprising:
- a flange comprising a shaft through opening for mounting on a propeller flange, a bearing housing section formed on a motor side end face of the flange, and a rotor bearing section formed on a propeller side end face of the flange;
- a rotor, which is mounted on a jacket wall of the rotor bearing section;
- and
- a stator comprising a bearing device and a torque support, wherein the bearing device is mounted on a jacket wall of the bearing housing section, and reaction torque is delivered to a structure of the aircraft via the torque support.
An electric drive for an aircraft hybrid system of an aircraft, the electric drive comprising:
- a flange comprising a shaft through opening for mounting on a propeller flange, a bearing housing section formed on a motor side end face of the flange, and a rotor bearing section formed on a propeller side end face of the flange;
- a rotor, which is mounted on a jacket wall of the rotor bearing section;
- and
- a stator comprising a bearing device and a torque support, wherein the bearing device is mounted on a jacket wall of the bearing housing section, and reaction torque is delivered to a structure of the aircraft via the torque support, wherein the flange comprises two parts, each of which delimits a section of the shaft through opening.
Dependencies are inferred from the claim text.