Electro-mechanically biased supercritical flight control surface loading to reduce high pressure actuation cycles

Patent metadata

Field	Value
Publication number	US-10793261-B2
Application number	US-201815952369-A
Country	US
Kind code	B2
Filing date	Apr 13, 2018
Priority date	Apr 13, 2018
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

An actuator assembly for an aircraft includes a support strut operatively coupled to a hinge axis of a flight control member of the aircraft, a hydraulic actuator operatively coupled to the flight control member via a pivot element, and an electro-mechanical actuator (EMA) having first and second opposing ends and a biasing member. The first end is operatively coupled to a support structure of the aircraft, and the second end is operatively coupled to both the support strut and the hydraulic actuator. The biasing member moves between a compressed state and an expanded state in response to a varying biasing load exerted on a surface of the flight control member, thereby reducing an amount of current needed to drive the EMA, as well as a number of high-pressure hydraulic cycles of the hydraulic actuator to control the flight control member.

First claim

What is claimed is:

1. An actuator assembly configured to control movement of a flight control member of an aircraft, the actuator assembly comprising:
a support strut operatively coupled to a hinge axis of a flight control member of an aircraft;
a hydraulic actuator coupled to the flight control member via a pivot element, and configured to pivot the flight control member about the hinge axis; and
an electro-mechanical actuator (EMA) comprising:
a first end operatively coupled to a support structure of the aircraft;
a second end, opposite the first end, operatively coupled to both the support strut and the hydraulic actuator; and
a biasing member configured to move between a compressed state and an expanded state responsive to a varying biasing load exerted on a surface of the flight control member.

2. The actuator assembly of claim 1 wherein the biasing member is configured to:
move to the compressed state responsive to an increase in the biasing load exerted on the surface of the flight control member; and
move to the expanded state responsive to a decrease in the biasing load exerted on the surface of the flight control member.

3. The actuator assembly of claim 2 wherein the support strut comprises a rigid, fixed length support member configured to:
translate motion of the flight control member to the biasing member responsive to the increase in the biasing load exerted on the flight surface; and
translate bias of the biasing member to the flight control member responsive to the decrease in the biasing load exerted on the flight surface.

4. The actuator assembly of claim 1 wherein the EMA further comprises first and second spaced-apart mount members, and wherein the biasing member is disposed between the first and second mount members and biases the first and second mount members away from each other.

5. The actuator assembly of claim 4 wherein the first mount member moves relative to the second mount member responsive to a biasing force exerted on the first mount member by the biasing member, and a compression force exerted on the first mount member by the support strut.

6. The actuator assembly of claim 1 wherein the hydraulic actuator comprises one or more ports configured to receive hydraulic fluid from a variable hydraulic system on the aircraft, and when in the compressed state, the biasing member is configured to reduce a number of high-pressure hydraulic cycles of the hydraulic actuator.

7. The actuator assembly of claim 1 wherein the biasing member is configured to reduce a current on an EMA motor that drives the EMA to move between a retracted state and an extended state.

8. The actuator assembly of claim 1 wherein the support strut, the hydraulic actuator, and the second end of the EMA pivot about a common axis when the biasing member moves between the compressed state and the expanded state.

9. An aircraft comprising:
a support structure;
a flight control member; and
an actuator assembly disposed between the support structure and the flight control member, the actuator assembly comprising:
a support strut operatively coupled to a hinge axis of the flight control member;
a hydraulic actuator coupled to the flight control member via a pivot element, and configured to pivot the flight control member about the hinge axis; and
an electro-mechanical actuator (EMA) comprising:
a first end operatively coupled to the support structure;
a second end, opposite the first end, operatively coupled to both the support strut and the hydraulic actuator; and
a biasing member configured to move between a compressed state and an expanded state responsive to a varying biasing load exerted on a surface of the flight control member.

10. The aircraft of claim 9 further comprising a distributed variable-pressure hydraulic system configured to selectively provide hydraulic fluid to the hydraulic actuator, and wherein the biasing member moves to the compressed state during a cycle in which the variable-pressure hydraulic system is not providing the hydraulic fluid to the hydraulic actuator.

11. The aircraft of claim 9 further comprising a control circuit configured to reduce a current to a motor that drives the EMA to move between a retracted state and an extended state.

12. The aircraft of claim 9 wherein the biasing member is configured to move to the compressed state when the biasing load exerted on the surface of the flight control member increases, and move to the expanded state when the biasing load exerted on the surface of the flight control member decreases.

13. The aircraft of claim 9 wherein the support strut comprises a rigid, fixed length support member configured to:
translate motion of the flight control member to the biasing member responsive to an increase in the biasing load exerted on the flight surface; and
translate a biasing force of the biasing member to the flight control member responsive to a decrease in the biasing load exerted on the flight surface.

14. The aircraft of claim 9 wherein the EMA further comprises first and second spaced-apart mount members, and wherein the biasing member is disposed between the first and second mount members and is configured to bias the first and second mount members away from each other.

15. A method of controlling a flight control member of an aircraft comprising a rigid support strut operatively coupled to a hinge axis of the flight control member, a hydraulic actuator operatively coupled to the flight control member via a pivot element, and an electro-mechanical actuator (EMA) comprising a biasing member and first and second terminals, wherein the first and second terminals are operatively coupled, respectively, to a support structure of the aircraft, and to both the support strut and the hydraulic actuator, the method comprising:
compressing the biasing member responsive to an increase in a biasing load exerted on a flight surface of the flight control member; and
expanding the biasing member responsive to a decrease in the biasing load exerted on the flight surface of the flight control member.

16. The method of claim 15 wherein compressing the biasing member comprises translating motion of the flight control member via the support strut to the biasing member responsive to the increase in the biasing load exerted on the flight surface.

17. The method of claim 16 wherein expanding the biasing member comprises translating a biasing force of the biasing member via the support strut to the flight control member responsive to the decrease in the biasing load exerted on the flight surface.

18. The method of claim 15 further comprising reducing a current needed by a motor that drives the EMA between a retracted state and an expanded state responsive to at least one of the biasing member compressing and expanding.

19. The method of claim 15 further comprising selectively providing hydraulic fluid to the hydraulic actuator using a distributed variable-pressure hydraulic system on the aircraft, and wherein compressing the biasing member comprises compressing the biasing member when the hydraulic system is not providing the hydraulic fluid.

20. The method of claim 15 further comprising reducing a number of high-pressure hydraulic cycles of the hydraulic actuator responsive to the biasing member compressing.

Assignees

• Boeing Co

Inventors

• Fox Michael Thomas
• Howell Eric Anton
• Roach Jeffrey M

Classifications

• B64C13/50

  using electrical energy · CPC title

• B64C13/40 Primary

  using fluid pressure · CPC title