Internal chamfering device and method

• US 9,517,511 B1
• Filed: 03/04/2013
• Issued: 12/13/2016
• Est. Priority Date: 05/09/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Gray, Everette D., Sisco, Farahnaz, Tsegga, Mekonnen
• Primary Examiner(s): Gates, Eric A
• Assistant Examiner(s): Janeski, Paul M
• Application Number:
  US13/784,442
• Time in Patent Office: 1,380 Days
• US Class Current: 1/1
• CPC Class Codes: B23B 2222/88 Titanium
• CPC Class Codes: B23B 2226/275 Carbon fibre reinforced carbon composites
• CPC Class Codes: B23B 2228/36 Multi-layered
• CPC Class Codes: B23B 2260/128 Sensors
• CPC Class Codes: B23B 29/034 with tools moving radially, e.g. for making chamfers or undercuttings
• CPC Class Codes: B23B 35/00 Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
• CPC Class Codes: B23B 51/101 Deburring tools B23B51/103 takes precedence
• CPC Class Codes: B23B 51/102 Back spot-facing or chamfering
• CPC Class Codes: B23C 2226/27 Composites, e.g. fibre reinforced composites
• CPC Class Codes: B23Q 17/2233 for adjusting the tool relative to the workpiece
• CPC Class Codes: Y10T 408/03 Processes
• CPC Class Codes: Y10T 408/8588 Axially slidable moving-means
• CPC Class Codes: Y10T 408/8734 including central Tool axially movable relative to support
• CPC Class Codes: Y10T 408/8738 including inverse cutting edge
• CPC Class Codes: Y10T 82/12 Radially moving rotating tool inside bore

Abstract

A method of forming an opening in a layered structure includes providing a layered structure including a first layer and a second layer and a near-zero gap interface defined between the first layer and the second layer; providing an opening through the layered structure such that the opening extends through the first layer and the second layer; and working simultaneously the opening in the fay surface of the first layer and the opening in the fay surface of the second layer without separating the first layer and the second layer. An internal chamfering device is also disclosed.

Claims

1. A method of forming an opening in a layered structure, comprising:

transmitting and receiving a signal to determine a location of an interface between a first fay surface of a first layer and a second fay surface of a second layer without separating the first and second layers, an aperture extending through at least a portion of the first layer and the second layer;

based on the location of the interface, working simultaneously the opening in the first fay surface of the first layer and the opening in the second fay surface of the second layer without separating the first layer and second layer, wherein prior to the transmitting and the receiving of the signal to determine the location of the interface, further comprising;

removing a first fastener from the aperture defined by the layered structure, the aperture comprising a first diameter;

boring the aperture to comprise a second diameter without separating the first and second layers, the second diameter greater than the first diameter;

the transmitting and the receiving of the signal to determine the location of the interface including determining the location of the interface between the first and second layers using an ultrasonic sensor; and

the working simultaneously of the opening including working the interface between the first and second layers to remove a burr created when boring the aperture.

2. The method of claim 1, wherein the layered structure comprises an aircraft wing or a fuselage component.

3. The method of claim 1, wherein the layered structure is coupled by a plurality of fasteners other than the first fastener.

4. The method of claim 1, further comprising inserting a second fastener into the aperture.

5. The method of claim 1, wherein the first layer comprises metal and the second layer comprises composite.

6. The method of claim 1, wherein the first layer and the second layer comprise a layered structure of an aircraft wing or a fuselage component.

7. A method of forming an opening in a layered structure, comprising:

transmitting and receiving a signal to determine a location of an interface between a first fay surface of a first layer and a second fay surface of a second layer without separating the first and second layers, an aperture extending through at least a portion of the first layer and the second layer, transmitting and receiving the signal comprises using a non-destructive instrument to determine the location; and

based on the location of the interface, working simultaneously the opening in the first fay surface of the first layer and the opening in the second fay surface of the second layer without separating the first layer and second layer, wherein the non-destructive instrument comprises using an ultrasonic sensor.

8. The method of claim 7, wherein working comprises deburring the opening in the first layer and the second layer.

9. The method of claim 7, wherein the first layer or the second layer comprises metal, composite, adhesive, or sealant.

10. The method of claim 7, wherein the first layer comprises metal and the second layer comprises composite.

11. The method of claim 7, wherein the first layer or the second layer comprises metal, composite, adhesive, or sealant.

12. The method of claim 7, wherein the first layer and the second layer comprise a layered structure of an aircraft wing or fuselage component.

13. A method of forming an opening in a layered structure, comprising:

transmitting and receiving a signal to determine a location of an interface between a first fay surface of a first layer and a second fay surface of a second layer without separating the first and second layers, an aperture extending through at least a portion of the first layer and the second layer;

based on the location of the interface, working simultaneously the opening in the first fay surface of the first layer and the opening in the second fay surface of the second layer without separating the first layer and second layer, wherein transmitting and receiving the signal comprises obtaining measurements using an ultrasonic sensor and averaging the measurements to determine the location.

14. The method of claim 13, wherein the measurements are obtained circumferentially around the aperture.

15. The method of claim 13, wherein working comprises deburring the opening in the first layer and the second layer.

16. The method of claim 13, wherein the first layer comprises metal and the second layer comprises composite.

17. The method of claim 13, wherein the first layer or the second layer comprises metal, composite, adhesive, or sealant.

18. A method of forming an opening in a layered structure, comprising:

transmitting and receiving a signal to determine a location of an interface between a first fay surface of a first layer and a second fay surface of a second layer without separating the first and second layers, an aperture extending through at least a portion of the first layer and the second layer; and

based on the location of the interface, working simultaneously the opening in the first fay surface of the first layer and the opening in the second fay surface of the second layer without separating the first layer and second layer, wherein prior to the transmitting and the receiving of the signal to determine the location of the interface, further comprising;

removing a first fastener from the aperture defined by the layered structure, the aperture comprising a first diameter, the layered structure being coupled by a second fastener;

boring the aperture to comprise a second diameter without separating the first and second layers, the second diameter greater than the first diameter;

the transmitting and the receiving of the signal to determine the location of the interface including determining a location of the interface between the first and second layers without removing the second fastener; and

the working simultaneously of the opening including working the interface between the first and second layers to remove a burr created when boring the aperture.

19. The method of claim 18, wherein transmitting and receiving the signal comprises using a non-destructive instrument to determine the location.

20. The method of claim 18, wherein the layered structure comprises an aircraft wing or a fuselage component.

21. The method of claim 18, wherein transmitting and receiving the signal includes determining the location of the interface between the first and second layers using an ultrasonic sensor.

22. The method of claim 18, wherein the first layer comprises metal and the second layer comprises composite.