Aircraft control surface actuation system with helical actuation path

• US 8,590,834 B1
• Filed: 11/14/2011
• Issued: 11/26/2013
• Est. Priority Date: 11/14/2011
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Nelson, Paul E.
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US13/295,187
• Time in Patent Office: 743 Days
• Field of Search: 244 992- 994, 244211-215, 244/218
• US Class Current: 244/99.3
• CPC Class Codes: B64C 13/32 using cam mechanisms

Abstract

An aircraft control surface actuation system including a wing member and an aircraft control surface hingedly connected to the wing member along a pivot axis, wherein the aircraft control surface is configured to axially move along the pivot axis when the aircraft control surface pivots relative to the wing member about the pivot axis.

Claims

1. An aircraft control surface actuation system comprising:

a wing member; and

an aircraft control surface pivotally connected to said wing member along a pivot axis,

wherein said aircraft control surface is configured to translate along said pivot axis relative to said wing member while simultaneously rotating about said pivot axis relative to said wing member.

2. The system of claim 1 further comprising at least one ball screw assembly between said wing member and said aircraft control surface.

3. The system of claim 2 wherein said ball screw assembly comprises a ball nut in threaded engagement with a ball screw.

4. The system of claim 3 wherein said wing member is connected to said ball nut and said aircraft control surface is connected to said ball screw.

5. The system of claim 1 further comprising at least one cam assembly between said wing member and said aircraft control surface.

6. The system of claim 5 wherein said cam assembly comprises a cam follower in camming engagement with a cam track slot, said cam track slot defining a helical path relative to said pivot axis.

7. The system of claim 6 wherein said wing member defines said cam track slot and said cam follower is connected to said aircraft control surface.

8. The system of claim 1 further comprising a power control unit configured to supply an axial force, said axial force causing said aircraft control surface to move relative to said wing member.

9. The system of claim 1 wherein said aircraft control surface is one of a flap, an aileron, an elevator, an elevon and a flaperon.

13. The system of claim 3 wherein said ball screw defines said pivot axis.

14. The system of claim 3 wherein said wing member is connected to said ball screw and said aircraft control surface is connected to said ball nut.

10. A method for actuating an aircraft control surface relative to a wing member, said method comprising the steps of:

connecting said aircraft control surface to said wing member along a pivot axis such that said aircraft control surface translate along said pivot axis while simultaneously rotating about said pivot axis; and

applying an axial force to said aircraft control surface to cause said aircraft control surface to move relative to said wing member.

11. The method of claim 10 wherein said connecting step comprises connecting said aircraft control surface to said wing member at a ball screw assembly.

12. The method of claim 10 wherein said connecting step comprises connecting said aircraft control surface to said wing member at a cam assembly, said cam assembly comprising a cam track slot that defines a helical path relative to said pivot axis.