Methods and apparatus for integrating rotary actuators in flight control systems

Patent metadata

Field	Value
Publication number	US-9950782-B2
Application number	US-201414529694-A
Country	US
Kind code	B2
Filing date	Oct 31, 2014
Priority date	Oct 31, 2014
Publication date	Apr 24, 2018
Grant date	Apr 24, 2018

Abstract

Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

First claim

The invention claimed is:

1. An apparatus comprising:
an aircraft structure;
first and second hinges coupled to said aircraft structure;
a control surface coupled to said first and second hinges;
a rotary actuator comprising a housing and an output shaft rotatable relative to said housing, the output shaft being coupled to said control surface for causing pivoting of said control surface about a hinge line;
a first reaction link having a first end rotatably coupled to said housing of said rotary actuator for transmitting reaction forces to said aircraft structure during pivoting of said control surface;
a second reaction link having a first end rotatably coupled to said housing of said rotary actuator for transmitting reaction forces to said aircraft structure; and
a hanger link having a first end rotatably coupled to respective second ends of said first and second reaction links and a second end rotatably coupled to said aircraft structure.

2. The apparatus as recited in claim 1 , wherein said aircraft structure comprises a fitting, said apparatus further comprising:
a pin coupled to a second end of said first reaction link; and
a spherical bearing that rotatably couples said fitting to said pin.

3. The apparatus as recited in claim 1 , wherein said aircraft structure comprises a fitting, said apparatus further comprising:
a pin coupled to said second end of said hanger link; and
a spherical bearing that rotatably couples said fitting to said pin.

4. The apparatus as recited in claim 1 , further comprising:
a pin;
a first spherical bearing that rotatably couples said first end of said hanger link to said pin;
a second spherical bearing that rotatably couples said second end of said first reaction link to said pin; and
a third spherical bearing that rotatably couples said second end of said second reaction link to said pin.

5. The apparatus as recited in claim 1 , wherein said output shaft of said rotary actuator has an axis of rotation parallel to said axis of rotation of said control surface, said apparatus further comprising an output crank that connects said output shaft to said control surface.

6. An apparatus comprising:
an aircraft structure comprising first and second ribs, wherein said second rib comprises a slot;
first and second hinges coupled to said aircraft structure;
a control surface coupled to said first and second hinges;
a rotary actuator comprising a housing and an output shaft rotatable relative to said housing, the output shaft being coupled to said control surface for causing pivoting of said control surface about a hinge line; and
a reaction link having a first end rotatably coupled to said housing of said rotary actuator for transmitting reaction forces to said aircraft structure during pivoting of said control surface;
first and second spherical bearings attached to said first rib;
a roller bearing seated in said slot of said second rib; and
a floating beam having one end connected to said first and second spherical bearings and another end connected to said roller bearing.

7. An apparatus comprising:
an aircraft structure;
first and second hinges coupled to said aircraft structure;
a control surface coupled to said first and second hinges;
a rotary actuator comprising a housing and an output shaft rotatable relative to said housing, wherein said output shaft of said rotary actuator has an axis of rotation perpendicular to said axis of rotation of said control surface, the output shaft being coupled to said control surface for causing pivoting of said control surface about a hinge line;
a reaction link having a first end rotatably coupled to said housing of said rotary actuator for transmitting reaction forces to said aircraft structure during pivoting of said control surface;
an output crank connected said output shaft; and
a push rod having one end rotatably coupled to said output crank and another end rotatably coupled to said control surface.

8. The apparatus as recited in claim 1 , wherein said aircraft structure comprises a wing and said control surface comprises an aileron.

9. The apparatus as recited in claim 8 , wherein said wing comprises a rear spar and first and second hinge ribs attached to said rear spar, said first and second hinges being attached to said first and second hinge ribs respectively.

10. An apparatus comprising:
an aircraft structure;
first and second hinges coupled to said aircraft structure;
a control surface coupled to said first and second hinges;
a rotary actuator comprising a housing and an output shaft rotatable relative to said housing, said output shaft being coupled to said control surface for causing rotation of said control surface about a hinge line;
a first reaction link having a first end rotatably coupled to said housing of said rotary actuator and a second end rotatably coupled to said aircraft structure during pivoting of said control surface; and
a second reaction link having a first end rotatably coupled to said housing of said rotary actuator and a second end rotatably coupled to said aircraft structure during pivoting of said control surface.

11. The apparatus as recited in claim 10 , wherein said aircraft structure comprises first and second fittings, said apparatus further comprising:
a first pin coupled to a second end of said first reaction link;
a first spherical bearing that rotatably couples said first fitting to said first pin;
a second pin coupled to a second end of said second reaction link; and
a second spherical bearing that rotatably couples said second fitting to said second pin.

12. The apparatus as recited in claim 10 , wherein said aircraft structure comprises first and second ribs, wherein said second rib comprises a slot, said apparatus further comprising:
first and second spherical bearings attached to said first rib;
a roller bearing seated in said slot of said second rib; and
a floating beam having one end connected to said first and second spherical bearings and another end connected to said roller bearing.

13. The apparatus as recited in claim 10 , wherein said aircraft structure comprises a wing and said control surface comprises an aileron.

14. A method for distributing reaction forces from a rotary actuator to an aircraft structure, comprising:
rotatably coupling a first end of a first reaction link to the housing of the rotary actuator;
rotatably coupling a second end of the first reaction link to a fitting of the aircraft structure;
rotatably coupling a second end of the reaction link to a fitting of the aircraft structure; and
rotatably coupling a second end of the reaction link to a fitting of the aircraft structure.

15. A method for distributing reaction forces from a rotary actuator to an aircraft structure, comprising:
hinging a control surface to an aircraft structure;
coupling an output shaft of a rotary actuator to the control surface;
linking a housing of the rotary actuator to the aircraft structure; and
operating the rotary actuator to cause pivoting of said control surface about a hinge line,
wherein said linking step comprises:
rotatably coupling respective first ends of first and second reaction links to the housing of the rotary actuator;
rotatably coupling respective second ends of the first and second reaction links to a first end of a pin;
rotatably coupling a first end of a hanger link to the pin; and
rotatably coupling a second end of the hanger link to a fitting of the aircraft structure.

16. The apparatus as recited in claim 10 , wherein said output shaft of said rotary actuator has an

Assignees

• Boeing Co

Inventors

• Huynh Neal Van
• Standley John A

Classifications

• B64C2009/005

  Ailerons · CPC title

• B64C9/00 Primary

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C13/28

  mechanical · CPC title

• B64C13/30 Primary

  using cable, chain, or rod mechanisms · CPC title