METHOD AND APPARATUS FOR REINFORCING COMPOSITE STRUCTURES

• US 20100065688A1
• Filed: 09/17/2007
• Published: 03/18/2010
• Est. Priority Date: 09/17/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Wood, Jeffrey H.
• Granted Patent: US 8,398,027 B2
• Time in Patent Office: Days
• US Class Current: 244/131
• CPC Class Codes: B29C 65/483 Reactive adhesives, e.g. chemically curing adhesives
• CPC Class Codes: B29C 65/562 using extra joining elements, i.e. which are not integral with the parts to be joined using plastic snap elements B29C65/58; using plastic rivets B29C65/601
• CPC Class Codes: B29C 66/54 Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form tubular articles
• CPC Class Codes: B29C 66/71 characterised by the composition of the plastics material of the parts to be joined welding bar compositions B29C65/125
• CPC Class Codes: B29C 66/721 Fibre-reinforced materials B29C66/729 takes precedence
• CPC Class Codes: B29C 66/7212 characterised by the composition of the fibres
• CPC Class Codes: B29C 66/72141 Fibres of continuous length
• CPC Class Codes: B29C 66/72525 comprising honeycomb cores
• CPC Class Codes: B29K 2063/00 Use of EP, i.e. epoxy resins or derivatives thereof, as moulding material
• CPC Class Codes: B29K 2105/06 containing reinforcements, fillers or inserts
• CPC Class Codes: B29K 2307/00 Use of elements other than metals as reinforcement
• CPC Class Codes: B29K 2307/04 Carbon
• CPC Class Codes: B29L 2031/608 Honeycomb structures
• CPC Class Codes: B29L 2031/727 Fastening elements bolts B29L2001/002; nuts B29L2001/005; screws B29L2001/007; slide fasteners B29L2005/00; buttons for haberdashery B29L2019/00
• CPC Class Codes: F16B 33/006 Non-metallic fasteners using screw-thread
• CPC Class Codes: Y10T 403/472 including mechanical interlock
• CPC Class Codes: Y10T 403/553 Laterally inserted section

Abstract

A computer implemented method and apparatus for creating a structural joint for an aircraft. A first composite component and a second composite component are co-joined to form the structural joint for the aircraft. A hole through the first composite component and the second composite component is created. A composite shear pin is placed through the hole. A composite collar is bonded to the composite shear pin with an adhesive.

Claims

1. A method for creating a structural joint for an aircraft, the method comprising:

co-joining a first composite component and a second composite component to form the structural joint for the aircraft;

creating a hole through the first composite component and the second composite component;

placing a composite shear pin through the hole; and

bonding a composite collar to the composite shear pin with an adhesive.

2. The method of claim 1, wherein the co-joining step comprises:

co-curing the first composite component to the second composite component.

3. The method of claim 1, wherein the co-joining step comprises:

co-bonding the first composite component to the second composite component.

4. The method of claim 1, wherein the co-joining step comprises:

bonding the first composite component to the second composite component with the adhesive.

5. The method of claim 1 further comprising:

mechanically locking the composite collar to the composite shear pin.

6. The method of claim 5, wherein the mechanically locking step comprises:

engaging a first mechanical feature for the composite collar to a second mechanical feature for the composite shear pin to mechanically lock the composite collar to the composite shear pin.

7. The method of claim 1, wherein the composite collar has a first mechanical feature and the composite shear pin has a second mechanical feature and wherein the bonding step comprises:

placing the adhesive between the first mechanical feature and the second mechanical feature, wherein the adhesive cures to bond the composite collar to the composite shear pin.

8. The method of claim 7, wherein the first mechanical feature is a set of internal annular grooves and the second mechanical feature is a set of external annular grooves.

9. A method for joining composite components, the method comprising:

co-joining a first composite component and a second composite component;

forming a channel through the first composite component and the second composite component; and

co-joining a composite fastener system in the channel.

10. The method of claim 9, wherein the step of co-joining the composite fastener system in the channel comprises:

applying an adhesive to a set of mechanical features in the composite fastener system to form an applied adhesive; and

curing the applied adhesive.

11. The method of claim 10 further comprising:

mechanically locking the composite fastener system in the channel.

12. The method of claim 9, wherein the composite fastener system comprises a pin and a collar.

13. The method of claim 11, wherein the step of-co-joining the composite fastener system in the channel comprises:

placing the pin into the channel;

positioning the collar relative to the pin in the channel;

applying adhesive in a space between a first mechanical feature for the collar and a second mechanical feature for the pin to form the applied adhesive; and

curing the applied adhesive.

14. The method of claim 12, wherein the step of-co-joining the composite fastener system in the channel further comprises:

applying the adhesive in the channel.

15. The method of claim 9, wherein the first composite component and the second composite component form a structural joint.

16. The method of claim 9, wherein the first composite component and the second composite component are part of a structure selected from one of an aircraft, a submarine, a spacecraft, a power plant, a building, and an automobile.

17. A joint comprising:

a first composite component;

a second composite component co-joined to the first composite component, wherein a channel through the first composite component and the second composite component is present;

a pin having a first end configured to prevent the first end from passing through the channel and a second end having a first mechanical feature;

a collar having a second mechanical feature; and

an adhesive located between the first mechanical feature of the pin and the second mechanical feature of the collar, wherein the adhesive bonds the pin to the collar.

18. The joint of claim 17, wherein the second mechanical feature is mechanically locked to the first mechanical feature.

19. The joint of claim 17, wherein the first mechanical feature and the second mechanical feature mechanically locks the pin to the collar.

20. The joint of claim 17, wherein the joint is located in a structure selected from one of—

an aircraft, a submarine, a spacecraft, a power plant, a building, and an automobile.