Actuator systems for flight control surface
AssigneeHoneywell International Inc.
InventorMichal Nozka
Life of this patent
Estimating the term…
Abstract
An actuator system for a flight control surface of an aerial vehicle includes a motor, and an inner shaft. The inner shaft includes a first portion at a first end and a second portion that extends from the first portion to a second end of the inner shaft. The first portion of the inner shaft is coupled to the motor. The second portion of the inner shaft is coupled to at least one roller that includes roller threads. The actuator system includes an inverted nut defining an inner bore and having an outer diameter that defines an output rod. The inner bore includes nut threads. The inverted nut is coupled about the inner shaft such that the nut threads are to engage with the plurality of roller threads to move the output rod, and the output rod is to be coupled to the flight control surface.
Claims19
An actuator system for a flight control surface of an aerial vehicle, comprising:
- a motor;
- an inner shaft including a first portion at a first end and a second portion that extends from the first portion to a second end of the inner shaft, the second end opposite the first end, the first portion of the inner shaft coupled to the motor and configured to be driven by the motor, the second portion of the inner shaft coupled to at least one roller configured to rotate with the inner shaft, the at least one roller including a plurality of roller threads;
- and
- an inverted nut defining an inner bore and having an outer diameter that defines an output rod, the output rod having a first nut end and an opposite second nut end, the inner bore extending from the first nut end to proximate the second nut end and including a plurality of nut threads, the inverted nut coupled about the inner shaft such that the plurality of nut threads are configured to engage with the plurality of roller threads to move the output rod relative to the inner shaft, and the second nut end defines a coupling flange that is configured to be coupled to the flight control surface;
- and
- an actuator housing that surrounds at least a portion of the inverted nut and the inner shaft, and the inverted nut is movable relative to the actuator housing,
- wherein the second nut end extends from the actuator housing.
An actuator system for a flight control surface of an aerial vehicle, comprising:
- a motor having a motor output shaft;
- a gearbox coupled to the motor output shaft and coupled to an inner shaft;
- the inner shaft including a first portion at a first end and a second portion that extends from the first portion to a second end of the inner shaft, the second end opposite the first end, the first portion of the inner shaft coupled to the gearbox and the inner shaft is configured to be driven by the gearbox, the second portion of the inner shaft including an inverted screw with a plurality of rollers, each of the plurality of rollers including a plurality of roller threads;
- an inverted nut defining an inner bore and having an outer diameter that defines an output rod, the output rod having a first nut end and an opposite second nut end, the inner bore extending from the first nut end to proximate the second nut end and including a plurality of nut threads, the inverted nut coupled about the inner shaft such that the plurality of nut threads are configured to engage with the plurality of roller threads to move the output rod relative to the inner shaft, and the second nut end defines a coupling flange that is configured to be coupled to the flight control surface;
- and
- an actuator housing that surrounds at least a portion of the inner shaft and the inverted nut, the inverted nut is movable relative to the actuator housing and the actuator housing is configured to be coupled to a frame of the aerial vehicle,
- wherein the second nut end extends from the actuator housing.
Dependencies are inferred from the claim text.