Actuator systems for flight control surface

Patent metadata

Field	Value
Publication number	US-12428135-B2
Application number	US-202318346559-A
Country	US
Kind code	B2
Filing date	Jul 3, 2023
Priority date	Jul 3, 2023
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

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.

First claim

What is claimed is:

1. 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.

2. The actuator system of claim 1 , wherein the motor includes a motor output shaft, a gearbox is coupled to the motor output shaft and coupled to the inner shaft, and the motor and the gearbox are disposed along a longitudinal axis of the actuator system.

3. The actuator system of claim 2 , wherein the gearbox is a multi-stage planetary gear box.

4. The actuator system of claim 1 , wherein the motor is disposed along an axis that is offset from a longitudinal axis of the actuator system.

5. The actuator system of claim 1 , wherein the actuator housing includes:
a wiper configured to remove debris from an outer surface of the inverted nut; and
a bushing configured to guide movement of the inverted nut.

6. The actuator system of claim 5 , wherein the actuator housing is configured to be coupled to a frame of the aerial vehicle.

7. The actuator system of claim 6 , wherein the actuator housing includes a first actuator housing and a second actuator housing, and the first actuator housing is configured to be coupled to the frame.

8. The actuator system of claim 5 , wherein the actuator housing includes a first actuator housing and a second actuator housing, the first actuator housing is received within the second actuator housing and the first actuator housing surrounds at least a portion of the motor.

9. The actuator system of claim 1 , wherein the at least one roller comprises a plurality of rollers that cooperate to define an inverted roller screw.

10. The actuator system of claim 1 , further comprising a sensor configured to observe a rotation of the inner shaft or a rotation of the motor to determine a position of the inverted nut.

11. The actuator system of claim 1 , further comprising a sensor configured to observe a position of the inverted nut.

12. The actuator system of claim 1 , further comprising at least one bearing coupled to the inner shaft.

13. 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.

14. The actuator system of claim 13 , wherein the motor and the gearbox are disposed along a longitudinal axis of the actuator system, and the gearbox is a planetary gear box.

15. The actuator system of claim 13 , wherein the motor is disposed along an axis that is offset from a longitudinal axis of the actuator system.

16. The actuator system of claim 13 , wherein the actuator housing includes:
a wiper configured to remove debris from an outer surface of the inverted nut; and
a bushing configured to guide movement of the inverted nut.

17. The actuator system of claim 13 , wherein the actuator housing includes a first actuator housing and a second actuator housing, the first actuator housing is received within the second actuator housing and the first actuator housing surrounds at least a portion of the gearbox and the motor.

18. The actuator system of claim 13 , wherein the actuator housing includes a first actuator housing and a second actuator housing, the first actuator housing surrounds at least a portion of the gearbox, and the first actuator housing is configured to be coupled to the frame.

19. The actuator system of claim 13 , further comprising a sensor configured to observe a rotation of the inner shaft or a rotation of the motor to determine a position of the inverted nut, and at least one bearing coupled to the inner shaft.

Assignees

• Honeywell Int Inc

Inventors

• Nozka Michal

Classifications

• F16H2025/228

  Screw mechanisms having rollers being supported by the screw shaft and engaging the nut · CPC title

• F16H2025/2087

  using planetary gears · CPC title

• F16H2025/2081

  Parallel arrangement of drive motor to screw axis · CPC title

• F16H2025/2031

  Actuator casings · CPC title

• F16H25/2418

  Screw seals, wipers, scrapers or the like · CPC title