WING DEBRIS DETECTOR

• US 20100012785A1
• Filed: 05/31/2007
• Published: 01/21/2010
• Est. Priority Date: 05/31/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Mackin, Steve G.
• Granted Patent: US 7,837,149 B2
• Time in Patent Office: Days
• US Class Current: 244/134.F
• CPC Class Codes: B64C 9/20 by multiple flaps
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

An apparatus and method for wind debris detection comprises a spring loaded probe that is deployed on the leading edge of an aircraft wing into an area where debris formation might impact wing aerodynamic performance. The probe travel is sensed by sensors (angular displacement, linear displacement, proximity, torque, load cell on spring, and the like), and if the sensor(s) detect that probe travel is limited then presence of debris is indicated.

Claims

1. A system for detecting wing debris on an aircraft having a wing main element, the system comprising:

a probe coupled to the wing main element;

a deployment mechanism coupled to the probe and configured to deploy the probe around a leading edge of the wing main element; and

a sensor coupled to the probe and configured to measure a deviation of the probe from an expected nominally deployed position.

2. The system according to claim 1, further comprising a controller coupled to the deployment mechanism and the sensor, wherein the controller is configured to control the probe.

3. The system according to claim 2, wherein the controller is further configured to:

deploy the probe for a first set of flight conditions; and

stow the probe for a second set of flight conditions.

4. The system according to claim 2, wherein the controller is further configured to determine presence of wing debris based upon the deviation.

5. The system according to claim 1, further comprising a spring coupled to the probe and the deployment mechanism, and configured to allow limited deflection of the probe from the expected position.

6. The system according to claim 5, wherein the sensor is further configured to measure load on the spring.

7. The system according to claim 1, wherein the sensor is further configured to measure if probe travel is limited.

8. The system according to claim 1, wherein the sensor is further configured to measure angular displacement of the probe.

9. The system according to claim 1, wherein the sensor is further configured to measure proximity between the probe and the wing debris.

10. The system according to claim 1, wherein the sensor is further configured to measure torque on the probe.

11. The system according to claim 1, further comprising a hinge for coupling the probe to the wing main element.

12. The system according to claim 10, wherein the sensor is further configured to measure angular displacement of the hinge.

13. The system according to claim 10, wherein the sensor is further configured to measure torque on the hinge.

14. A method for detecting wing debris on an aircraft having a wing main element and a probe coupled to the wing main element, the method comprising:

deploying the probe in front of a leading edge of the wing main element;

measuring a position of the probe; and

indicating presence of wing debris if the position of the probe deviates from an expected position by at least a threshold amount.

15. The method according to claim 14, further comprising signaling presence of wing debris if the presence of debris is indicated.

16. The method according to claim 15, wherein the signaling further comprises notifying a pilot of the aircraft.

17. The method according to claim 14, wherein the deploying step is initiated by a pilot of the aircraft.

18. The method according to claim 14, wherein the deploying step is initiated automatically in response to a flight condition of the aircraft.

19. The method according to claim 14, further comprising stowing the probe in the wing main element.

20. The method according to claim 19, wherein the stowing step is initiated by a pilot of the aircraft.

21. The method according to claim 20, wherein the stowing step is initiated automatically in response to a flight condition of the aircraft.

22. A system for detecting presence of debris on an aircraft wing comprising a leading edge and a Krueger flap coupled to the leading edge, the system comprising:

a probe coupled to the aircraft wing, the probe having a measurement tip;

a deployment mechanism coupled to the probe and configured to move the probe upon deployment of the Krueger flap such that the measurement tip of the probe extends between a gap formed between the Krueger flap and the leading edge, and to bias the measurement tip toward the leading edge until travel of the measurement tip is limited and the measurement tip reaches a measurement position; and

a sensing architecture coupled to the probe and configured to compare the measurement position to an expected debris-free position.

23. The system according to claim 22, wherein the sensing architecture is configured to indicate the presence of debris on the leading edge when the measurement position deviates from the expected debris-free position by at least a threshold amount.