Aircraft wing flap skew detection systems and methods

Patent metadata

Field	Value
Publication number	US-10017273-B2
Application number	US-201615334347-A
Country	US
Kind code	B2
Filing date	Oct 26, 2016
Priority date	Oct 26, 2016
Publication date	Jul 10, 2018
Grant date	Jul 10, 2018

Abstract

A flap skew detection system is configured to detect flap skew of one or more flaps moveably secured to one or more wings of an aircraft. The flap skew detection system includes a flap support assembly that couples a flap to a wing. The flap support assembly includes a fixed portion that is configured to secure to the wing, a moveable portion that is moveably coupled to the fixed portion and configured to securely support the flap, and a link moveably coupled to the fixed portion and the moveable portion. The link includes a cylinder defining an internal chamber including a hydraulic fluid chamber, a piston having a piston head within the internal chamber, and hydraulic fluid retained within the hydraulic fluid chamber. A pressure detector is fluidly coupled to the hydraulic fluid chamber. The pressure detector is configured to detect a fluid pressure of the hydraulic fluid pressure within the hydraulic fluid chamber. The fluid pressure detected by the pressure detector is used to determine existence of flap skew.

First claim

What is claimed is:

1. A flap skew detection system that is configured to detect flap skew of one or more flaps moveably secured to one or more wings of an aircraft, the flap skew detection system comprising:
a flap support assembly that couples a flap to a wing, the flap support assembly including:
a fixed portion that is configured to secure to the wing;
a moveable portion that is moveably coupled to the fixed portion, wherein the moveable portion is configured to securely support the flap;
a link moveably coupled to the fixed portion and the moveable portion, wherein the link includes: (a) a cylinder defining an internal chamber including a hydraulic fluid chamber, (b) a piston having a piston head within the internal chamber, and (c) hydraulic fluid retained within the hydraulic fluid chamber; and
a pressure detector fluidly coupled to the hydraulic fluid chamber, wherein the pressure detector is configured to detect a fluid pressure of the hydraulic fluid pressure within the hydraulic fluid chamber, wherein the fluid pressure detected by the pressure detector is used to determine existence of flap skew.

2. The flap skew detection system of claim 1 , further comprising a flap skew detection unit in communication with the pressure detector, wherein the flap skew detection unit receives a pressure signal indicative of the fluid pressure from the pressure detector, and wherein the flap skew detection unit determines the existence of flap skew through an analysis of the pressure signal.

3. The flap skew detection system of claim 2 , wherein the flap skew detection unit is configured to compare the pressure signal to another pressure signal output from another pressure detector coupled to another flap support assembly that is coupled to the flap or another flap in order to determine the existence of flap skew.

4. The flap skew detection system of claim 2 , wherein the flap skew detection unit outputs a flap skew alert signal upon determining that flap skew exists.

5. The flap skew detection system of claim 1 , wherein the fixed portion comprises a support bracket that is configured to secure to the wing.

6. The flap skew detection system of claim 1 , wherein the moveable portion comprises a carrier fitting that is moveably coupled to the fixed portion.

7. The flap skew detection system of claim 1 , wherein the pressure detector comprises a pressure switch.

8. The flap skew detection system of claim 1 , wherein the pressure detector comprises a pressure sensor.

9. The flap skew detection system of claim 1 , further comprising a fluid fitting coupled to the cylinder, wherein the fluid fitting is configured to allow fluid to be input into the hydraulic fluid chamber, and wherein the fluid fitting is configured to allow for testing of the pressure detector.

10. The flap skew detection system of claim 1 , wherein the hydraulic fluid is incompressible grease.

11. A flap skew detection method that is configured to detect flap skew of one or more flaps moveably secured to one or more wings of an aircraft, the flap skew detection method comprising:
securing a fixed portion of a flap support assembly to a wing;
moveably coupling a moveable portion of the flap support assembly to the fixed portion;
securely supporting the flap with the moveable portion;
moveably coupling a link to the fixed portion and the moveable portion;
positioning a piston head of a piston within an internal chamber of the link;
retaining hydraulic fluid within a hydraulic fluid chamber of the internal chamber;
fluidly coupling a pressure detector to the hydraulic fluid chamber;
detecting a fluid pressure of the hydraulic fluid within the hydraulic fluid chamber with the pressure detector; and
determining existence of flap skew through the detecting the fluid pressure.

12. The flap skew detection method of claim 11 , further comprising:
communicatively coupling a flap skew detection unit to the pressure detector;
receiving, by the flap skew detection unit, a pressure signal indicative of the fluid pressure from the pressure detector; and
wherein the determining comprises analyzing, by the flap skew detection unit, the pressure signal to determine the existence of flap skew.

13. The flap skew detection method of claim 12 , wherein the analyzing comprises comparing the pressure signal to another pressure signal output from another pressure detector coupled to another flap support assembly that is coupled to the flap or another flap in order to determine the existence of flap skew.

14. The flap skew detection method of claim 12 , further comprising outputting, by the flap skew detection unit, a flap skew alert signal upon determining that flap skew exists.

15. The flap skew detection method of claim 11 , wherein the fixed portion comprises a support bracket that is configured to secure to the wing.

16. The flap skew detection method of claim 11 , wherein the moveable portion comprises a carrier fitting that is moveably coupled to the fixed portion.

17. The flap skew detection method of claim 11 , wherein the pressure detector comprises a pressure switch, or a pressure sensor.

18. The flap skew detection method of claim 11 , further comprising:
inputting fluid into the hydraulic fluid chamber fitting via a fluid fitting coupled to a cylinder defining an internal chamber including the hydraulic fluid chamber; and
testing the pressure detector based, at least in part, on the inputting.

19. An aircraft comprising:
a fuselage;
a first wing outwardly extending from the fuselage;
a first flap moveably secured to the first wing;
a second wing outwardly extending from the fuselage opposite from the first wing;
a second flap moveably secured to the first wing; and
a flap skew detection system that is configured to detect flap skew of the first and second flaps, the flap skew detection system comprising flap support assemblies that couple to the first and second flaps, wherein each of the flap support assemblies includes:
a fixed support bracket that fixed to one of the first or second wings;
a moveable carrier fitting that is moveably coupled to the fixed support bracket, wherein the carrier fitting securely support one of the first or second flaps;
a link moveably coupled to the support bracket and the carrier fitting, wherein the link includes: (a) a cylinder defining an internal chamber including a hydraulic fluid chamber, (b) a piston having a piston head within the internal chamber, and (c) an incompressible hydraulic fluid retained within the hydraulic fluid chamber;
a pressure detector fluidly coupled to the hydraulic fluid chamber, wherein the pressure detector is configured to detect a fluid pressure of the hydraulic fluid pressure within the hydraulic fluid chamber, wherein the fluid pressure detected by the pressure detector is used to determine existence of flap skew of one or both of the first and second flaps; and
a fluid fitting coupled to the cylinder, wherein the fluid fitting is configured to allow fluid to be input into the hydraulic fluid chamber, and wherein the fluid fitting is configured to allow for testing of the pressure detector.

20. The aircraft of claim 19 , wherein the flap skew detection system further comprises a flap skew detection unit in communication with the pressure detector, wherein the flap skew detection unit receives a pressure signal indicative of the fluid pressure from the pressure detector, wherein the flap skew detection unit determines the existence of flap skew through an analysis of

Assignees

• Boeing Co

Inventors

• Jones Kelly Thomas

Classifications

• G01M5/0016

  of aircraft wings or blades · CPC title

• B64D45/0005 Primary

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• B64D2045/001

  for indicating symmetry of flaps deflection · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B64C9/16

  at the rear of the wing · CPC title