Controlling airloads on aircraft folding wing tips

Patent metadata

Field	Value
Publication number	US-2017190410-A1
Application number	US-201614988202-A
Country	US
Kind code	A1
Filing date	Jan 5, 2016
Priority date	Jan 5, 2016
Publication date	Jul 6, 2017
Grant date	—

Abstract

Example apparatus and methods are disclosed herein for moving control surfaces on an aircraft wing to control airloads during a wing tip folding operation (from a folded position to an extended position or from an extended position to a folded position). An example method includes determining a position of a control surface on a wing of an aircraft. In the example method, the wing has a fixed wing portion and a wing tip moveably coupled to the fixed wing portion. The example method includes determining a change in the position of the control surface from a first position to second position for facilitating movement of the wing tip while the aircraft is not in flight. The example method also includes moving the control surface to the second position and moving the wing tip between an extended position and a folded position.

First claim

What is claimed is:

1 . A method comprising:
determining a position of a control surface on a wing of an aircraft, the wing having a fixed wing portion and a wing tip moveably coupled to the fixed wing portion; determining, via a processor, a change in the position of the control surface from a first position to a second position for facilitating movement of the wing tip while the aircraft is not in flight; moving the control surface to the second position; and moving the wing tip between an extended position and a folded position.

2 . The method of claim 1 , wherein the control surface is an aileron on the fixed wing portion of the wing adjacent the wing tip.

3 . The method of claim 2 , wherein if the wing tip is to be moved from the extended position to the folded position, the second position of the aileron is a faired position or a trailing edge down position.

4 . The method of claim 1 , wherein the control surface directs less air toward the wing tip when in the second position than when in the first position.

5 . The method of claim 1 , further including:
determining, via the processor, a speed of the aircraft; and preventing the determining of the change and the moving of the control surface if the speed is above a trigger speed.

6 . The method of claim 1 , further including:
determining, via the processor, if moving the control surface to the second position is adverse to a pilot command; and moving the control surface to the second position if the pilot command is an air brake command, or preventing the moving of the control surface to the second position if the pilot command is a roll command.

7 . The method of claim 1 , wherein the control surface is a first control surface, and further including:
determining a position of a second control surface on the fixed wing portion; determining, via the processor, a change in the position of the second control surface from a third position to a fourth position for facilitating movement of the wing tip while the aircraft is not in flight; and moving the second control surface to the third position.

8 . The method of claim 7 , wherein the first control surface is an aileron and the second control surface is a leading edge slat.

9 . An apparatus comprising:
a processor configured to:
determine whether a control surface on a wing of an aircraft can be moved from a non-advantageous position to an advantageous position based on a control law, the wing having a fixed wing portion and wing tip moveably coupled to the fixed wing portion; and
generate an instruction to move the control surface to the advantageous position based on whether the control surface can be moved;
a first controller to be communicatively coupled to a first actuator, the first actuator coupled to the control surface, the first controller to generate a control signal, in response to the instruction, to move the control surface from the non-advantageous position to the advantageous position; and a second controller to be communicatively coupled to a second actuator to move the wing tip in accordance with a wing tip movement operation.

10 . The apparatus of claim 9 , wherein the control law is based on a speed of the aircraft, and, to determine whether the control surface can be moved, the processor is to:
determine the speed of the aircraft; compare the speed to a trigger speed; and send the instruction to the first controller if the speed is below is the trigger speed, or prevent movement of the control surface to the advantageous position if the speed is above the trigger speed.

11 . The apparatus of claim 9 , wherein the control law is based on a pilot command, and wherein, if the pilot command is a symmetric command, the processor is to send the instruction to the first controller, or if the pilot command is an asymmetric command, the processor is to prevent movement of the control surface to the advantageous position.

12 . The apparatus of claim 9 , wherein the wing tip movement operation is a transition from an extended position to a folded position.

13 . The apparatus of claim 12 , wherein the control surface directs less air toward the wing tip when in the advantageous position than when in the non-advantageous position.

14 . The apparatus of claim 12 , wherein the control surface is a leading edge slat.

15 . The apparatus of claim 14 , wherein the advantageous position of the leading edge slat is a deployed position.

16 . An aircraft comprising;
a wing having a fixed wing portion and a wing tip moveably coupled to the fixed wing portion; a control surface on the wing; and an aircraft control system configured to:
determine a position of the control surface;
determine whether the position of the control surface is an advantageous position or a non-advantageous position for folding the wing tip; and
if the control surface is in the non-advantageous position, generate a control signal to move the control surface to the advantageous position.

17 . The aircraft of claim 16 , wherein the control surface is an aileron on the fixed wing portion of the wing adjacent the wing tip.

18 . The aircraft of claim 17 , wherein the non-advantageous position is a trailing edge up position of the aileron and the advantageous position is a faired position or a trailing edge down position of the aileron.

19 . The aircraft of claim 16 , wherein the control surface is an aileron on the wing tip.

20 . The aircraft of claim 19 , wherein the non-advantageous position is a trailing edge up position of the aileron and the advantageous position is a faired position or a trailing edge down position of the aileron.

Assignees

• Boeing Co

Inventors

• Good Mark Steven
• Paul Jonathan J

Classifications

• B64C2009/005

  Ailerons · CPC title

• B64C3/36 Primary

  Structures adapted to reduce effects of aerodynamic or other external heating · CPC title

• B64C9/10 Primary

  one surface adjusted by movement of another, e.g. servo tabs (B64C9/04 takes precedence; adjusting surfaces of different type or function B64C9/12) · CPC title

• B64C13/00

  Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers · CPC title

• B64C9/24

  by single flap · CPC title