Rotary actuator for flight control surface

Patent metadata

Field	Value
Publication number	US-2025146562-A1
Application number	US-202418595790-A
Country	US
Kind code	A1
Filing date	Mar 5, 2024
Priority date	Nov 6, 2023
Publication date	May 8, 2025
Grant date	—

Abstract

A rotary actuator for a flight control surface includes a first electric motor connected to a first geartrain having planetary gearsets in series and a first drive gear driven by the first electric motor via the first geartrain. The first geartrain and the first drive gear define a first powertrain. The rotary actuator also includes a second electric motor connected to a second geartrain having planetary gearsets in series. The second geartrain is separate from the first geartrain. The rotary actuator further includes a second drive gear driven by the second electric motor via the second geartrain. The second geartrain and the second drive gear define a second powertrain that is coaxial with the first powertrain. Additionally, the rotary actuator includes an output shaft parallel to the first and second powertrains. The output shaft is driven simultaneously via the first and second drive gears.

First claim

What is claimed is:

1 . A rotary actuator for a flight control surface, comprising:
a first electric motor drivably connected to a first geartrain having at least two planetary gearsets arranged in series; a first drive gear driven by the first electric motor via the first geartrain, wherein the first geartrain and the first drive gear define a first powertrain; a second electric motor drivably connected to a second geartrain having at least two planetary gearsets arranged in series, wherein the second geartrain is separate from the first geartrain; a second drive gear driven by the second electric motor via the second geartrain, wherein the second geartrain and the second drive gear define a second powertrain that is arranged coaxially with the first powertrain; and an output shaft driven simultaneously via the first drive gear and the second drive gear.

2 . The rotary actuator of claim 1 , wherein the first electric motor and the second electric motor are axially adjacent to each other.

3 . The rotary actuator of claim 2 , wherein the first drive gear and the second drive gear are arranged at axial outer ends of the first powertrain and the second powertrain, respectively.

4 . The rotary actuator of claim 1 , wherein the first and second geartrains each comprise three planetary gearsets.

5 . The rotary actuator of claim 1 , wherein the output shaft is configured to rotate less than one revolution.

6 . The rotary actuator of claim 1 , wherein the output shaft further comprises:
a first sector gear arranged at a first end of the output shaft and engaged with the first drive gear; and a second sector gear arranged at a second end of the output shaft and engaged with the second drive gear.

7 . A rotary actuator for moving a flight control surface of an aircraft, comprising:
a first electric motor drivably connected to a first geartrain having a plurality of planetary gearsets arranged in series; a first drive gear driven by the first electric motor via the first geartrain, wherein the first geartrain and the first drive gear define a first powertrain; and an output shaft arranged parallel to the first powertrain and configured to be driven by the first drive gear.

8 . The rotary actuator of claim 7 , wherein a full stroke of the rotary actuator prompts less than a full revolution of the output shaft.

9 . The rotary actuator of claim 7 , wherein the output shaft further comprises:
a first sector gear that is engaged with the first drive gear.

10 . The rotary actuator of claim 7 , further comprising:
a second electric motor drivably connected to a second geartrain having at least one gearset; and a second drive gear driven by the second electric motor via the second geartrain, wherein the second geartrain and the second drive gear define a second powertrain, wherein the second powertrain is operably coupled with the output shaft, such that the first and second powertrains are configured to simultaneously drive the output shaft.

11 . The rotary actuator of claim 10 , wherein the at least one gearset comprises:
at least one planetary gearset.

12 . The rotary actuator of claim 11 , wherein the at least one planetary gearset comprises:
a plurality of planetary gearsets arranged in series.

13 . The rotary actuator of claim 10 , wherein the first and second electric motors are axially adjacent to each other.

14 . The rotary actuator of claim 13 , wherein the first geartrain is axially adjacent the first electric motor opposite the second electric motor.

15 . The rotary actuator of claim 14 , wherein the second geartrain is axially adjacent the second electric motor opposite the first electric motor.

16 . The rotary actuator of claim 7 , wherein the first geartrain comprises three planetary gearsets.

17 . A rotary actuator, comprising:
a first powertrain that includes a first electric motor, a first geartrain operably coupled with the first electric motor and having at least one gearset, and a first drive gear operably coupled with the first electric motor via the first geartrain; a second powertrain that includes a second electric motor, a second geartrain operably coupled with the second electric motor and having at least one gearset, and a second drive gear operably coupled with the second electric motor via the second geartrain, wherein the first electric motor is positioned axially adjacent to the second electric motor, the first geartrain is positioned axially adjacent to the first electric motor, and the second geartrain is positioned axially adjacent to the second electric motor, such that the first and second electric motors are positioned axially between the first and second geartrains; and an output shaft arranged parallel to the first and second powertrains and configured to be driven by the first and second powertrains.

18 . The rotary actuator of claim 17 , wherein the at least one gearset of the first geartrain comprises at least one planetary gearset, and the at least one gearset of the second geartrain comprises at least one planetary gearset.

19 . The rotary actuator of claim 18 , wherein the at least one planetary gearset of the first geartrain comprises a plurality of planetary gearsets arranged in series, and the at least one planetary gearset of the second geartrain comprises a plurality of planetary gearsets arranged in series.

20 . The rotary actuator of claim 17 , wherein driven rotation of the output shaft is configured to move a flight control surface of an aircraft.

Assignees

• Schaeffler Technologies Ag

Inventors

• Sturgin Todd
• Hooker Craig
• Hrusch Nicholas

Classifications

• B64C13/505 Primary

  having duplication or stand-by provisions · CPC title

• F16H1/46

  Systems consisting of a plurality of gear trains each with orbital gears, {i.e. systems having three or more central gears} · CPC title

• B64C13/50

  using electrical energy · CPC title

• F16H19/08 Primary

  for interconverting rotary motion and oscillating motion · CPC title