Multi-directional load joint system

• US 8,985,515 B2
• Filed: 12/28/2010
• Issued: 03/24/2015
• Est. Priority Date: 12/28/2010
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Textron Innovations Incorporated (Textron Inc)
• Inventors: McCullough, John R., Carlson, David Gordon, Hethcock, James Donn, Oldroyd, Paul K., May, Carl A.
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Dixon, Keith L
• Application Number:
  US13/641,369
• Publication Number:
  US 20130026297A1
• Time in Patent Office: 1,547 Days
• Field of Search: 244/131, 244/132, 244/119, 298/973
• US Class Current: 244/131
• CPC Class Codes: B29C 65/4835 Heat curing adhesives
• CPC Class Codes: B29C 65/5021 being multi-layered
• CPC Class Codes: B29C 65/5057 positioned between the surfaces to be joined B29C65/5035 takes precedence
• CPC Class Codes: B29C 65/5078 and being composed by several elements
• CPC Class Codes: B29C 65/5085 and comprising grooves, e.g. being E-shaped, H-shaped
• 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 66/1122 Single lap to lap joints, i.e. overlap joints B29C66/45, B29C66/472, B29C66/52272 take precedence
• CPC Class Codes: B29C 66/1142 Single butt to butt joints
• CPC Class Codes: B29C 66/1162 Single bevel to bevel joints, e.g. mitre joints
• CPC Class Codes: B29C 66/1282 comprising at least one overlap joint-segment
• CPC Class Codes: B29C 66/12881 comprising at least two monotone curved joint-segments
• CPC Class Codes: B29C 66/43441 with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
• CPC Class Codes: B29C 66/721 Fibre-reinforced materials B29C66/729 takes precedence
• CPC Class Codes: B29C 66/72525 comprising honeycomb cores
• CPC Class Codes: B29C 66/8416 of different thickness
• CPC Class Codes: B29D 99/001 Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings articles with hollow walls B29D24/00
• CPC Class Codes: B29L 2031/3076 Aircrafts blades, propellers B29L2031/08
• CPC Class Codes: B64C 1/06 Frames; Stringers; Longerons ; Fuselage sections
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: F16B 5/01 : by means of fastening elements specially adapted for honeycomb panels
• CPC Class Codes: F16B 5/12 : Fastening strips or bars to sheets or plates, e.g. rubber strips, decorative strips for motor vehicles, by means of clips friction- grip releasable fastenings in general F16B2/00; fastening rods or tubular parts to flat surfaces at an angle F16B9/00
• CPC Class Codes: Y02T 50/40 : Weight reduction
• CPC Class Codes: Y10T 29/49622 : Vehicular structural member making
• CPC Class Codes: Y10T 403/70 : Interfitted members

Abstract

A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

Claims

1. A joint system for attaching a panel to a skin, the system comprising:

a first member having a first leg portion, a first inner base portion, and a first outer base portion, the first outer base portion and the first inner base portion being coupled to the skin along a first bonding surface; and

a second member having a second leg portion, a second inner base portion, and a second outer base portion, the second inner base portion and the second outer base portion of the second member being coupled to the first inner base portion of the first member;

wherein the first inner base portion separates the second member from the skin, the first inner base portion extending underneath the second inner member and the second outer member of the second member, the first inner base portion being coupled to the second member along a second bonding surface;

wherein the panel is coupled to the first leg portion and the second leg portion.

2. The joint system according to claim 1, wherein at least one of the first inner base portion, the first outer base portion, the second inner base portion, and the second outer base portion is tapered.

3. The joint system according to claim 1, wherein the first member and the second member are coupled to the skin with adhesive.

4. The joint system according to claim 1, wherein the first member and the second member are coupled to the skin with at least one fastener.

5. The joint system according to claim 1, wherein the panel is coupled to the first leg portion and the second leg portion with an adhesive.

6. The joint system according to claim 1, wherein the panel is coupled to the first leg portion and the second leg portion with at least one fastener.

7. The joint system according to claim 1, wherein the first member and the second member are approximately “

T”

shaped.

8. The joint system according to claim 1, further comprising:

at least one fastener located through the first inner base portion, the second inner base portion, and the skin.

9. The joint system according to claim 1, wherein the skin is a panel structural member.

10. A joint system for attaching a panel to a skin, the system comprising:

a first member having a first leg portion, a first inner base portion, and a first outer base portion, the first outer base portion and the first inner base portion being coupled to the skin along a first bonding surface; and

a second member having a second leg portion, a second inner base portion, and a second outer base portion, the second outer base portion and the second inner base portion being coupled to the first inner base portion along a second bonding surface, second member being separated from the skin by the first member, the first inner portion extending underneath the outer base portion of the second member;

wherein the panel is coupled to the first leg portion and the second leg portion; and

;

wherein the panel is capable of being coupled to the first leg portion and the second leg portion while the first bonding surface and the second bonding surface are in contact with the skin.

11. The joint system according to claim 10, further comprising:

a gap between the first inner base portion and the second inner base portion.

12. The joint system according to claim 10, wherein the second inner base portion is approximately parallel to the first inner base portion.

13. The joint system according to claim 10, wherein the first member and the second member are approximately “

T”

shaped.

14. The joint system according to claim 10, wherein the panel is a structural member in an aircraft.

15. A method of assembling a structural joint system, comprising:

coupling a first member to a skin so that the first member is rigidly associated with the skin, the first member comprising;

a first base portion;

a first leg portion extending from the first base portion;

preparing a second member for adhesive bonding, the second member comprising;

a second base portion;

a second leg portion extending from the second base portion;

bonding the second member to an upper surface of the first base portion such that the second base portion is separated from the skin, the first base portion extending between the second base portion and the skin; and

bonding a structural member between the first leg portion and the second leg portion;

wherein while bonding the second member to the first member the first leg portion remains parallel to the second leg portion.

16. The method according to claim 15, wherein first leg portion and the first base portion are positioned approximately 90 degrees to each other.

17. The method according to claim 15, wherein the step of bonding the second member to the skin and to the first member, and step of bonding the structural member between the first leg portion and the second leg portion, occur approximately in the same procedure.

18. The method according to claim 15, wherein bonding the structural member between the first leg portion and the second leg portion involves using adhesive film and moving the second leg portion towards the first leg portion so as to prevent the adhesive film from being displaced.

19. The method according to claim 15, further comprising:

using a fastener between the overlapping portion of the first base portion and the second base portion in order to apply pressure during curing of an adhesive located there between.