Telescoping track system for aerodynamic surfaces

Patent metadata

Field	Value
Publication number	US-11845536-B2
Application number	US-202117385603-A
Country	US
Kind code	B2
Filing date	Jul 26, 2021
Priority date	Jul 26, 2021
Publication date	Dec 19, 2023
Grant date	Dec 19, 2023

Abstract

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

First claim

What is claimed is:

1. An aerodynamic surface actuation system, comprising:
a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks;
a plurality of outer tracks, each comprising a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and
an actuator comprising an actuator arm and configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages, wherein the plurality of linkages comprise:
a first linkage connected to the actuator arm and connected to at least two intermediate tracks of the plurality of intermediate tracks; and
a second linkage connected to the actuator arm and connected to the middle track.

2. The aerodynamic surface actuation system of claim 1 , wherein the aerodynamic surface comprises a slat or a flap of an aircraft wing.

3. The aerodynamic surface actuation system of claim 1 , wherein the middle track comprises a plurality of bearing pads configured to provide an interface between the middle track and the plurality of intermediate tracks.

4. The aerodynamic surface actuation system of claim 1 , wherein:
each respective intermediate track of the plurality of intermediate tracks comprises:
at least one inner bearing pad configured to provide a first interface between the respective intermediate track and a flange of a respective outer track of the plurality of outer tracks; and
at least one outer bearing pad configured to provide a second interface between the respective intermediate track and an inner surface of the middle track, and

each respective intermediate track of the plurality of intermediate tracks is configured to move along at least one outer track of the plurality of outer tracks.

5. The aerodynamic surface actuation system of claim 1 , wherein the plurality of outer tracks are mounted to one or more longitudinal structural elements in an aerodynamic structure.

6. The aerodynamic surface actuation system of claim 5 , wherein:
the aerodynamic structure comprises a wing of an aircraft, and
the one or more longitudinal structural elements comprise ribs within the wing.

7. The aerodynamic surface actuation system of claim 1 , wherein:
the first linkage of the plurality of linkages is connected to the actuator arm at a first distance from an axis of rotation of the actuator arm, and
the second linkage of the plurality of linkages is connected to the actuator arm at a second distance from the axis of rotation of the actuator arm.

8. The aerodynamic surface actuation system of claim 1 , wherein:
the middle track comprises an I-shaped cross-section,
each intermediate track of the plurality of intermediate tracks comprises a C-shaped cross-section, and
each outer track of the plurality of outer tracks comprises a T-shaped cross-section.

9. The aerodynamic surface actuation system of claim 1 , wherein when in a fully retracted position, no part of the aerodynamic surface actuation system extends beyond a wing spar.

10. The aerodynamic surface actuation system of claim 1 , wherein the actuator is configured to move the middle track and the plurality of intermediate tracks along a curvilinear path between a plurality of set positions.

11. The aerodynamic surface actuation system of claim 1 , further comprising:
a position sensor configured to sense a position of the middle track, the plurality of outer tracks, or the aerodynamic surface; and
a processing system configured to control the actuator.

12. An aerodynamic surface actuation system, comprising:
a plurality of first tracks, wherein each first track of the plurality of first tracks:
comprises a flange, and
is mounted to a longitudinal structural element in an aerodynamic structure;

a plurality of second tracks, wherein each respective second track of the plurality of second tracks:
comprises a channel configured to receive a flange of at least one first track of the plurality of first tracks,
comprises one or more inner bearing pads configured to provide an interface between the channel of the respective second track and the flange of the at least one first track, and
comprises one or more outer bearing pads configured to provide an interface between the respective second track and a third track; and

the third track connected to an aerodynamic surface and configured to interface with and move along a plurality of outer surfaces of at least two second tracks of the plurality of second tracks, wherein the third track comprises one or more inner bearing pads configured to provide interfaces between the third track and the at least two second tracks; and
an actuator arm configured to control a position of the third track and a position of the plurality of second tracks via a plurality of linkages,
wherein a first linkage of the plurality of linkages is connected to the actuator arm and connected to at least two second tracks of the plurality of second tracks, and
wherein a second linkage of the plurality of linkages is connected to the actuator arm and connected to the third track.

13. The aerodynamic surface actuation system of claim 12 , wherein:
the first linkage is connected to the actuator arm at a first distance from an axis of rotation of the actuator arm, and
the second linkage of the plurality of linkages is connected to the actuator arm at a second distance from the axis of rotation of the actuator arm.

14. The aerodynamic surface actuation system of claim 12 , wherein when in a fully retracted position, no part of the aerodynamic surface actuation system extends beyond a wing spar.

15. The aerodynamic surface actuation system of claim 12 , wherein the actuator arm is configured to move the third track and the plurality of second tracks along a curvilinear path between a plurality of set positions.

16. A method of actuating an aerodynamic surface, comprising:
moving, using an actuator, a middle track connected to an aerodynamic surface along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track interface with one or more outer surfaces of the plurality of intermediate tracks; and
moving, using the actuator, the plurality of intermediate tracks along a plurality of outer tracks,
wherein each outer track of the plurality of outer tracks comprises a flange configured to interface with one or more inner surfaces of the plurality of intermediate tracks,
wherein the actuator moves the middle track and moves the intermediate tracks via an actuator arm and a plurality of linkages,
wherein a first linkage connected to the actuator arm and connected to at least two intermediate tracks of the plurality of intermediate tracks, and
wherein a second linkage connected to the actuator arm and connected to the middle track.

17. The method of claim 16 , wherein the actuator is configured to move the middle track and the plurality of intermediate tracks along a curvilinear path between a plurality of set positions.

18. The method of claim 17 , wherein the plurality of set positions comprises a fully extended position, a fully retracted position, and positions in between the fully extended and fully retracted positions.

19. The method of claim 16 , further comprising:
sensing a position of the middle track, the plurality of outer tracks, or the aer

Assignees

• Boeing Co

Inventors

• Edmunds Matthew
• Hoffenberg Robert
• Santini Gregory M
• Walker Steven P

Classifications

• B64C13/30 Primary

  using cable, chain, or rod mechanisms · CPC title

• B64C3/187

  Ribs · CPC title

• B64C9/14

  forming slots · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C13/38

  with power amplification · CPC title