Systems and methods for controlling aircraft flaps and spoilers

• US 7,338,018 B2
• Filed: 02/04/2005
• Issued: 03/04/2008
• Est. Priority Date: 02/04/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Huynh, Neal V., Pepper, Ralph Scott, Bleeg, Robert J., Bocksch, Brian L., Standley, John A.
• Primary Examiner(s): SWIATEK, ROBERT P
• Application Number:
  US11/051,738
• Publication Number:
  US 20060175468A1
• Time in Patent Office: 1,124 Days
• Field of Search: 244210-217, 244 991- 993
• US Class Current: 244/215
• CPC Class Codes: B64C 9/16 at the rear of the wing
• CPC Class Codes: B64C 9/323 associated with wings
• CPC Class Codes: B64D 2045/001 for indicating symmetry of flaps deflection
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Systems and methods for controlling aircraft flaps and spoilers. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned proximate to the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.

Claims

1. An aircraft wing system, comprising:

a wing having a trailing edge;

a flap positioned proximate to the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position;

a first actuator operatively coupled to the flap to move the flap between the first flap position and the second flap position;

a spoiler positioned at least proximate to the flap, the spoiler being movable among at least three positions including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position in which the spoiler is deflected downwardly from the first spoiler position, and a third spoiler position in which the spoiler is deflected upwardly from the first spoiler position;

a second actuator operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions mechanically independently of the motion of the flap; and

a controller operatively coupled to the first and second actuators, wherein the controller is configured to direct the spoiler, independently of the flap, to the first spoiler position during cruise, the second spoiler position during take-off and landing, and the third spoiler position during speed-braking and roll maneuvers.

2. The system of claim 1 wherein the second actuator is connected to the wing and includes a coupling connected to the spoiler, and wherein the wing does not include a fairing that houses the coupling.

3. The system of claim 1 wherein the flap is mechanically coupled to the wing, and the spoiler is mechanically coupled to the wing, but the spoiler is not mechanically connected directly to the flap.

4. The system of claim 1 wherein the second actuator is configured to release a force applied to the spoiler allowing the spoiler to be driven by direct mechanical contact with the flap from the second spoiler position to the first spoiler position as the flap moves from the second flap position to the first flap position.

5. The system of claim 1 wherein the wing has a trailing edge and a chord line and wherein the flap is a single flap positioned proximate to the wing trailing edge at the chord line.