Actuator for use in aviation
AssigneeZF Friedrichshafen AG
InventorsJürgen Götte, Uwe Arnold
Life of this patent
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Abstract
The present embodiments provide an actuator for a rotor blade adjustment having an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.
Claims20
An actuator for a rotor blade adjustment, comprising:
- an electromechanical drive unit connected with an output drive via a gearbox;
- wherein the drive unit comprises at least two partial drives that can be operated independently from one another;
- and
- wherein the gearbox is located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.
An actuator for aviation applications, the actuator comprising:
- a drive unit having at least a first partial drive and a second partial drive;
- a gearbox connected to the drive unit;
- and
- an output drive connected to the gearbox;
- wherein the first partial drive is located on a first side of the gearbox, and wherein the second partial drive is located on a second side of the gearbox.
A method for operating an actuator for a rotor blade adjustment, the method comprising:
- operating a first partial drive of the actuator located on a first side of a gearbox, wherein the gearbox connects the first partial drive to an output drive;
- wherein the actuator comprises a second partial drive located on a second side of the gearbox, and wherein the second partial drive is separated from the first partial drive.
Dependencies are inferred from the claim text.