Aircraft flight control system including electromechanical actuator

Patent metadata

Field	Value
Publication number	US-11235862-B2
Application number	US-202016744214-A
Country	US
Kind code	B2
Filing date	Jan 16, 2020
Priority date	Jul 18, 2017
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

Abstract

An aircraft flight control system includes a first actuator attached to a wing main body, a horn arm configured to transmit an output of the first actuator to a control surface, and a second actuator that is a rotary actuator and attached to the control surface. At least one of the first actuator and the second actuator is an electromechanical actuator (EMA). A first end of the horn arm is coupled to an output terminal of the first actuator, and a second end of the horn arm is fixed to an output terminal of the second actuator. The second actuator is attached to the control surface such that a turning axis of the output terminal is parallel to or coincides with a fulcrum axis (hinge line) of the control surface.

First claim

The invention claimed is:

1. An aircraft flight control system comprising:
a wing main body and a control surface of an aircraft;
a first actuator attached to the wing main body;
a control surface arm member that transmits an output of the first actuator to the control surface; and
a second actuator that is a rotary actuator, wherein:
at least one of the first actuator and the second actuator is an electromechanical actuator (EMA);
a first end of the control surface arm member is coupled to an output terminal of the first actuator;
a second end of the control surface arm member is fixed to an output terminal of the second actuator; and
the second actuator is attached to the control surface such that a turning axis of the output terminal of the second actuator is parallel to or coincides with a fulcrum axis of the control surface.

2. The aircraft flight control system according to claim 1 , wherein:
the first actuator is a linear actuator; and
the first end of the control surface arm member is directly coupled to the output terminal of the first actuator.

3. The aircraft flight control system according to claim 1 , wherein:
the first actuator is a rotary actuator; and
the first end of the control surface arm member is indirectly coupled to the output terminal of the first actuator through a coupler.

4. The aircraft flight control system according to claim 3 , wherein the coupler includes:
a coupling arm member fixed to the output terminal of the first actuator; and
an inter-arm coupling member coupling the coupling arm member and the first end of the control surface arm member.

5. The aircraft flight control system according to claim 1 , wherein the second actuator is an EMA.

6. The aircraft flight control system according to claim 1 , wherein in a case that the first actuator is an EMA, the first actuator includes an output terminal lock that locks an operation of the output terminal of the first actuator.

7. The aircraft flight control system according to claim 6 , wherein the output terminal lock includes a motor shaft brake.

8. The aircraft flight control system according to claim 6 , wherein the output terminal lock includes a reduction gear.

9. The aircraft flight control system according to claim 1 , wherein in a case that the second actuator is an EMA, the second actuator includes an output terminal lock that locks an operation of the output terminal of the second actuator.

10. The aircraft flight control system according to claim 9 , wherein the output terminal lock includes a motor shaft brake.

11. The aircraft flight control system according to claim 9 , wherein the output terminal lock includes a reduction gear.

12. The aircraft flight control system according to claim 1 , wherein the first actuator is an EMA and the second actuator is an electrohydraulic actuator (EHA).

13. An aircraft flight control system comprising:
a first actuator;
a horn arm that transmits an output of the first actuator to a control surface of an aircraft; and
a second actuator that is a rotary actuator, wherein:
a first end of the horn arm is coupled to a first output terminal of the first actuator;
a second end of the horn arm is fixed to a second output terminal of the second actuator; and
the second actuator is attached to the control surface such that a turning axis of the second output terminal is parallel to or coincides with a fulcrum axis of the control surface.

14. The aircraft flight control system according to claim 13 , wherein at least one of the first actuator and the second actuator is an electromechanical actuator (EMA).

15. The aircraft flight control system according to claim 13 , wherein at least one of the first actuator and the second actuator is an electrohydraulic actuator (EHA).

16. The aircraft flight control system according to claim 13 , wherein the first actuator is a linear actuator.

17. The aircraft flight control system according to claim 16 , wherein the first end of the horn arm is directly coupled to the first output terminal of the first actuator.

18. The aircraft flight control system according to claim 13 , wherein:
the first actuator is a rotary actuator;
the first end of the horn arm is coupled to a coupler; and
the coupler is coupled to the first output terminal of the first actuator.

19. The aircraft flight control system according to claim 17 , wherein the coupler includes:
a coupling arm fixed to the first output terminal of the first actuator; and
an inter-arm coupling member that couples the coupling arm and the first end of the horn arm.

20. A system comprising:
a first rotary actuator including a first output terminal;
a second rotary actuator including a second output terminal;
a horn arm that transmits an output of the first rotary actuator to a control surface, the horn arm including a first end that is coupled to the first output terminal, and a second end that is coupled to the second output terminal;
a coupling arm that is fixed to the first output terminal; and
an inter-arm that couples the coupling arm to the first end of the horn arm, wherein
the second rotary actuator is attached to the control surface such that a turning axis of the second output terminal coincides with a fulcrum axis of the control surface.

Assignees

• Kawasaki Heavy Ind Ltd

Inventors

• Miyazono Kohei
• Nishiyama Yoji
• Sugiura Hideyuki

Classifications

• F16H21/12

  for conveying rotary motion · CPC title

• B64C13/50 Primary

  using electrical energy · CPC title

• B64C13/341

  having duplication or stand-by provisions · CPC title

• B64C13/30

  using cable, chain, or rod mechanisms · CPC title

• F16H21/16

  for interconverting rotary motion and reciprocating motion · CPC title