Apparatuses and methods for joining composite members and other structural members in aircraft wing boxes and other structures

• US 7,575,194 B2
• Filed: 11/30/2006
• Issued: 08/18/2009
• Est. Priority Date: 11/30/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U., Brown, Stephen T.
• Primary Examiner(s): Mansen; Michael R
• Assistant Examiner(s): BROOKMAN, STEPHEN A
• Application Number:
  US11/607,333
• Publication Number:
  US 20080128553A1
• Time in Patent Office: 992 Days
• Field of Search: 244/120, 244/123.1, 244/123.13, 244/123.5, 244/123.6, 244/123.7, 244/123.8, 244/123.9, 244/131, 244/133, 244/119, 244/124, 403/187, 403/230, 403/188, 403/262, 522/72, 522/821
• US Class Current: 244/123.1
• CPC Class Codes: B64C 1/26 Attaching the wing or tail units or stabilising surfaces

Abstract

Apparatuses and methods for joining composite members and other structural members in aircraft wings and other structures. An aircraft wing box structure configured in accordance with one embodiment of the invention includes a first composite member having a first surface portion positioned at an angel relative to a second surface portion of a second composite member. The wing box structure of this embodiment further includes at least one metallic joining member having an upstanding leg portion extending from a base portion. The base portion of the joining member is bonded to the first surface portion of the first composite member with a first portion of adhesive, and the upstanding leg portion of the metallic joining member is bonded to the second surface portion of the second composite member with a second portion of adhesive.

Claims

1. An aircraft structure comprising:

a first structural member constructed from composite materials, the first structural member having a tapered edge portion, wherein the tapered edge portion has a first surface portion opposite a second surface portion;

a second structural member having a third surface portion, wherein the tapered edge portion of the first structural member at least approximately abuts the third surface portion of the second structural member;

a first metallic joining member having a first base portion positioned adjacent to the third surface portion of the second structural member, and a first upstanding leg portion positioned adjacent to the first surface portion of the first structural member, wherein at least a first distal end portion of the first upstanding leg portion is tapered;

a second metallic joining member having a second base portion positioned adjacent to the third surface portion of the second structural member, and a second upstanding leg portion positioned adjacent to the second surface portion of the first structural member, wherein at least a second distal end portion of the second upstanding leg portion is tapered, and wherein the first base portion of the first metallic joining member is sandwiched between the second base portion of the second metallic joining member and the second structural member;

a first portion of adhesive forming a first structural bond between the first upstanding leg portion of the first metallic joining member and the first surface portion of the first structural member; and

a second portion of adhesive forming a second structural bond between the second upstanding leg portion of the second metallic joining member and the second surface portion of the first structural member.

2. The aircraft structure of claim 1, further comprising:

a third portion of adhesive forming a third structural bond between the first base portion of the first metallic joining member and the third surface portion of the second structural member; and

a fourth portion of adhesive forming a fourth structural bond between the second base portion of the second metallic joining member and the first base portion of the first metallic joining member.

3. The aircraft structure of claim 1 wherein the tapered edge portion of the first structural member is bonded to the first upstanding leg portion of the first metallic joining member and the second upstanding leg portion of the second metallic joining member in the absence of any structural fasteners extending through the first and second upstanding leg portions and the tapered edge portion.

4. The aircraft structure of claim 1 wherein the first structural member includes a first core portion sandwiched between a first facesheet and a second facesheet, and wherein the second structural member includes a second core portion sandwiched between a third facesheet and a fourth facesheet.

5. The aircraft structure of claim 1 wherein the tapered edge portion of the first structural member is a first tapered edge portion, wherein the first structural member further includes a second tapered edge portion opposite from the first tapered edge portion, and wherein the second tapered edge portion has a fourth surface portion opposite a fifth surface portion, and wherein the aircraft structure further comprises:

a third structural member having a sixth surface portion, wherein the second tapered edge portion of the first structural member at least approximately abuts the sixth surface portion of the third structural member;

a third metallic joining member having a third base portion positioned adjacent to the sixth surface portion of the third structural member, and a third upstanding leg portion positioned adjacent to the fourth surface portion of the first structural member, wherein at least a third distal end portion of the third upstanding leg portion is tapered;

a fourth metallic joining member having a fourth base portion positioned adjacent to the sixth surface portion of the third structural member, and a fourth upstanding leg portion positioned adjacent to the fifth surface portion of the first structural member, wherein at least a fourth distal end portion of the fourth upstanding leg portion is tapered;

a third portion of adhesive forming a third structural bond between the third upstanding leg portion of the third metallic joining member and the fourth surface portion of the first structural member; and

a fourth portion of adhesive forming a fourth structural bond between the fourth upstanding leg portion of the fourth metallic joining member and the fifth surface portion of the first structural member.

6. The aircraft structure of claim 1 wherein the first structural member is a wing rib and the second structural member is a wing spar.

7. The aircraft structure of claim 1 wherein the first structural member is a wing rib and the second structural member is a first wing spar, wherein the tapered edge portion of the wing rib is a first tapered edge portion and the wing rib further includes a second tapered edge portion opposite from the first tapered edge portion, and wherein the second tapered edge portion has a fourth surface portion opposite a fifth surface portion, and wherein the aircraft structure further comprises:

a second wing spar having a sixth surface portion, wherein the second tapered edge portion of the wing rib at least approximately abuts the sixth surface portion of the second wing spar;

a third metallic joining member having a third base portion positioned adjacent to the sixth surface portion of the second wing spar, and a third upstanding leg portion positioned adjacent to the fourth surface portion of the wing rib, wherein at least a third distal end portion of the third upstanding leg portion is tapered;

a fourth metallic joining member having a fourth base portion positioned adjacent to the sixth surface portion of the second wing spar, and a fourth upstanding leg portion positioned adjacent to the fifth surface portion of the wing rib, wherein at least a fourth distal end portion of the fourth upstanding leg portion is tapered;

a third portion of adhesive forming a third structural bond between the third upstanding leg portion of the third metallic joining member and the fourth surface portion of the wing rib; and

a fourth portion of adhesive forming a fourth structural bond between the fourth upstanding leg portion of the fourth metallic joining member and the fifth surface portion of the wing rib.

8. An aircraft structure comprising:

a first structural member having a tapered core portion sandwiched between a first facesheet and a second facesheet, wherein the first facesheet has a first surface portion and the second facesheet has an opposite second surface portion, wherein the first and second surface portions meet to form a tapered edge along an outer boundary of the first structural member;

a second structural member having a third surface portion, wherein the tapered edge of the first structural member at least approximately abuts the third surface portion of the second structural member;

a first metallic joining member having a first base portion positioned adjacent to the third surface portion of the second structural member, and a first upstanding leg portion positioned adjacent to the first surface portion of the first structural member, wherein at least a first distal end portion of the first upstanding leg portion is tapered;

a second metallic joining member having a second base portion positioned adjacent to the third surface portion of the second structural member, and a second upstanding leg portion positioned adjacent to the second surface portion of the first structural member, wherein at least a second distal end portion of the second upstanding leg portion is tapered;

wherein the tapered edge of the first structural member is sandwiched between the first upstanding leg portion and the second upstanding leg portion, and wherein the first base portion of the first metallic joining member is sandwiched between the second base portion of the second metallic joining member and the second structural member;

a first portion of adhesive forming a first structural bond between the first upstanding leg portion of the first metallic joining member and the first surface portion of the first structural member; and

a second portion of adhesive forming a second structural bond between the second upstanding leg portion of the second metallic joining member and the second surface portion of the first structural member.