Track roller failure detection systems and methods

Patent metadata

Field	Value
Publication number	US-10053237-B2
Application number	US-201615161066-A
Country	US
Kind code	B2
Filing date	May 20, 2016
Priority date	May 20, 2016
Publication date	Aug 21, 2018
Grant date	Aug 21, 2018

Abstract

Systems and methods are provided for a track roller failure detection system. The system may include a main aerodynamic device and a secondary aerodynamic device including a track supported by one or more rollers and a marker. Failure of the one or more rollers may result in the track contacting the marker. Operation of the secondary aerodynamic device when one or more of the rollers have failed may result in the marker leaving a mark and/or a trail on a portion of the main aerodynamic device and/or a portion of the secondary aerodynamic device. Failure of the one or more rollers may then be determined from the mark and/or trail.

First claim

What is claimed is:

1. An aircraft aerodynamic device comprising:
a main aerodynamic body;
a secondary aerodynamic body;
a roller coupled to the main aerodynamic body;
a track connected to the secondary aerodynamic body, configured to be coupled to the roller, and configured to slide by contacting the roller to move the secondary aerodynamic body relative to the main aerodynamic body; and
a marker configured to indicate a failure of the roller, wherein the marker comprises at least one of:
soapstone, synthetic welding marker, and/or paint crayon configured to mark the track responsive to the failure of the roller;
a compound configured to react with a coating of the track, the track comprising the coating; or
an electrical apparatus configured to form a circuit responsive to the failure of the roller.

2. The aircraft aerodynamic device of claim 1 , further comprising a plurality of markers, each marker configured to indicate a failure of the roller for an associated failure mode, wherein the markers comprise the soapstone, the synthetic welding marker, and/or the paint crayon.

3. The aircraft aerodynamic device of claim 2 , wherein the aircraft aerodynamic device comprises at least a first marker and a second marker and wherein the first marker and the second marker are disposed on opposite sides of the track.

4. The aircraft aerodynamic device of claim 3 , wherein the first marker is disposed below the track and the second marker is disposed above the track.

5. The aircraft aerodynamic device of claim 1 , wherein the track comprises the coating, wherein the markers comprise the compound configured to react with the coating of the track, and wherein the aircraft aerodynamic device comprises a plurality of rollers.

6. The aircraft aerodynamic device of claim 5 , wherein the aircraft aerodynamic device comprises at least three rollers, each configured to be coupled to the track to allow the track to move along a first path.

7. The aircraft aerodynamic device of claim 1 , wherein the secondary aerodynamic body comprises a slat and the track comprises a slat track, a flap, and/or a droop nose.

8. The aircraft aerodynamic device of claim 1 , further comprises a secondary load element configured to support the track responsive to the failure of the roller, wherein the marker comprises the electrical apparatus configured to form the circuit responsive to the failure of the roller.

9. The aircraft aerodynamic device of claim 1 , wherein the marker is further configured to support the track responsive to the failure of the roller.

10. The aircraft aerodynamic device of claim 1 , wherein the track comprises a first section configured to slide by contacting the roller and a second section configured to be marked responsive to the track decoupling from the roller.

11. The aircraft aerodynamic device of claim 1 , wherein the marker is configured to mark the track and/or the secondary aerodynamic body responsive to a failure of the roller.

12. The aircraft aerodynamic device of claim 1 , wherein the marker is an embedded marker and/or a bonded marker.

13. The aircraft aerodynamic device of claim 1 , wherein the track comprises a first end and a second end and the aircraft aerodynamic device further comprises a fuel tank disposed behind the first end.

14. An aircraft comprising the aircraft aerodynamic device of claim 1 , wherein the aircraft comprises:
a fuselage;
the aerodynamic device coupled to the fuselage; and
an aircraft propulsor coupled to the aerodynamic device and/or the fuselage.

15. A method of operating the aircraft aerodynamic device of claim 1 , the method comprising:
moving the secondary aerodynamic body by sliding the track on the roller; and
indicating the failure of the roller with the marker.

16. The method of claim 15 , wherein the track and/or the secondary aerodynamic body is marked by the marker responsive to the failure of the roller.

17. A method of manufacturing the aircraft aerodynamic device of claim 1 , the method comprising:
coupling the roller to the main aerodynamic body;
coupling the secondary aerodynamic body to the roller via coupling the track to the roller; and
coupling the marker to the main aerodynamic body.

18. The method of claim 15 , wherein the secondary aerodynamic body contacts the marker responsive to failure of the roller.

19. An aircraft aerodynamic device comprising: a main aerodynamic body; a secondary aerodynamic body; a roller coupled to the main aerodynamic body; a track connected to the secondary aerodynamic body, configured to be coupled to the roller, and configured to slide by contacting the roller to move the secondary aerodynamic body relative to the main aerodynamic body; and a marker configured to indicate a failure of the roller, the marker comprising soapstone, synthetic welding marker, and/or paint crayon and configured to mark the track responsive to the failure of the roller.

20. An aircraft aerodynamic device comprising: a main aerodynamic body; a secondary aerodynamic body; a roller coupled to the main aerodynamic body; a track comprising a coating, connected to the secondary aerodynamic body, configured to be coupled to the roller, and configured to slide by contacting the roller to move the secondary aerodynamic body relative to the main aerodynamic body; and a marker configured to indicate a failure of the roller, the marker comprising a compound and configured to contact the track responsive to the failure of the roller to react with the coating.

Assignees

• Boeing Co

Inventors

• Huang Sam X
• Jones Kelly T

Classifications

• B64C3/38

  Adjustment of complete wings or parts thereof · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B64F5/40 Primary

  Maintaining or repairing aircraft · CPC title

• B64C9/00

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• B64C2009/005

  Ailerons · CPC title