초록 ▼

Apparatuses and methods for joining structural members. In one embodiment, an apparatus for joining a first member to a second member includes a first part and a second part configured to be engaged with and bonded to the first part. In one aspect of this embodiment, the first part includes a first

Apparatuses and methods for joining structural members. In one embodiment, an apparatus for joining a first member to a second member includes a first part and a second part configured to be engaged with and bonded to the first part. In one aspect of this embodiment, the first part includes a first surface facing a first direction, a second surface facing a second direction different than the first direction, a first recess at least proximate to the first surface, and a second recess at least proximate to the second surface. In another aspect of this embodiment, the second part includes a third surface facing a third direction, a fourth surface facing a fourth direction different than the third direction, a first protuberance at least proximate to the third surface, and a second protuberance at least proximate to the fourth surface. In yet another aspect of this embodiment, the first protuberance is configured to be received by the first recess, and the second protuberance is configured to be received by the second recess, when the second part is engaged with the first part to join the structural members.

대표청구항 ▼

1. An apparatus comprising:a first aircraft member; a second aircraft member; a first part attached to the first aircraft member, the first part having at least two sets of associated flange portions, wherein each set of associated flange portions has a first surface facing a first direction and a s

1. An apparatus comprising:a first aircraft member; a second aircraft member; a first part attached to the first aircraft member, the first part having at least two sets of associated flange portions, wherein each set of associated flange portions has a first surface facing a first direction and a second surface facing a second direction different than the first direction, each set of associated flange portions further having a first recess at least proximate to the first surface and a second recess at least proximate to the second surface; and at least a second part attached to the second aircraft member, the second part configured to be engaged with one of the sets of associated flange portions of the first part, the second part having a third surface facing a third direction and a fourth surface facing a fourth direction different than the third direction, the second part further having a first protuberance at least proximate to the third surface and a second protuberance at least proximate to the fourth surface, wherein the first protuberance is configured to be received by the first recess of the one set of associated flange portions, and the second protuberance is configured to be received by the second recess of the one set of associated flange portions, and wherein the third and fourth surfaces of the second part are configured to receive adhesive for bonding the second part to the one set of associated flange portions of the first part. 2. The apparatus of claim 1 wherein the first part includes a base portion with at least a fifth surface attached to the first aircraft member, and wherein the second part includes at least a sixth surface attached to the second aircraft member.3. The apparatus of claim 1 wherein the first part includes a base portion with at least a fifth surface bonded to the first aircraft member, and wherein the second part includes at least a sixth surface bonded to the second member.4. The apparatus of claim 1 wherein the first part includes a base portion with at least a fifth surface configured for attachment to the first member, and wherein the second part includes an aperture configured to receive a fastener for attaching the second member to the second part.5. The apparatus of claim 1 wherein the first part includes a base portion with at least a fifth surface attached to the first aircraft member, wherein the first and second surfaces are positioned at angles of from about 85 degrees to about 90 degrees relative to the fifth surface, and wherein the second part includes at least a sixth surface attached to the second aircraft member, the sixth surface being at least generally parallel to the third and fourth surfaces.6. The apparatus of claim 1 wherein the first part includes a base portion, and wherein the first recess is positioned at an intersection between the first surface and the base portion and the second recess is positioned at an intersection between the second surface and the base portion.7. The apparatus of claim 1 wherein the first part further includes a first base portion attached to the first aircraft member.8. The apparatus of claim 1 wherein the first part further includes a first base portion configured to be attached to the first aircraft member, and wherein the second part further includes an aperture configured to receive a fastener for attaching the second aircraft member to the second part.9. The apparatus of claim 1 wherein the first part further includes a first base portion bonded to the first aircraft member, and wherein the second part is bonded to the second aircraft member.10. The apparatus of claim 1 wherein the first part has two sets of associated flange portions, and wherein the apparatus further comprises a third part configured to be engaged with one of the sets of associated flange portions of the first part, wherein the first part includes a base portion bonding the first part to the first aircraft member, wherein the second part is bonded to the second aircraft member, and wherein the third part is configured to be bonded to a third aircraft member.11. The apparatus of claim 1 wherein the first part has three sets of associated flange portions, and wherein the apparatus further comprises a third part and a fourth part, wherein each of the second, third and fourth parts are configured to be engaged with one of the sets of associated flange portions of the first part, and wherein the second part is bonded to the second aircraft member, the third part is bonded to a third aircraft member, and the fourth part is configured to be bonded to a fourth aircraft member.12. The apparatus of claim 1 wherein the first part has four sets of associated flange portions, and wherein the apparatus further comprises a third part, a fourth part, and a fifth part, wherein each of the second, third, fourth, and fifth parts are configured to be engaged with one of the sets of associated flange portions of the first part, and wherein the second part is configured to be bonded to the second aircraft member, the third part is configured to be bonded to a third aircraft member, the fourth part is configured to be bonded to a fourth aircraft member, and the fifth part is configured to be bonded to a fifth aircraft member.13. The apparatus of claim 1 wherein the first and second surfaces of the first part are elastically moveable relative to each other.14. The apparatus of claim 1 wherein the first part includes a base portion, and wherein the first recess is positioned at an intersection between the first surface and the base portion and the second recess is positioned at an intersection between the second surface and the base portion.15. The apparatus of claim 1 wherein each of the flange portions are tapered.16. An apparatus comprising:a first aircraft member; a second aircraft member; a first part having a first base portion and first and second flange portions projecting from the first base portion, wherein the first flange portion includes a first surface facing a first direction and the second flange portion includes a second surface facing a second direction different than the first direction, the first part further having a first recess at least proximate to the first surface and a second recess at least proximate to the second surface, wherein the first base portion includes a first base surface with adhesive bonding the first part to the first aircraft member; and a second part configured to be engaged with the first part, the second part having a second base portion and third and fourth flange portions projecting from the second base portion, wherein the third flange portion includes a third surface facing a third direction and the fourth flange portion includes a fourth surface facing a fourth direction different than the third direction, the second part further having a first protuberance at least proximate to the third surface and a second protuberance at least proximate to the fourth surface, wherein the second base portion includes a second base surface with adhesive bonding the second part to the second aircraft member, and wherein the third surface is configured to receive adhesive for bonding the third surface to the first surface, the fourth surface is configured to receive adhesive for bonding the fourth surface to the second surface, the first protuberance is configured to be received by the first recess, and the second protuberance is configured to be received by the second recess when the second part is engaged with the first part. 17. The apparatus of claim 16 wherein the first and second surfaces of the first part are elastically moveable relative to each other.18. The apparatus of claim 16 wherein the third and fourth surfaces of the second part are elastically moveable relative to each other.19. The apparatus of claim 16 wherein the first and second surfaces of the first part are elastically moveable relative to each other, and the third and fourth surfaces of the second part are elastically moveable relative to each other.20. The apparatus of claim 16 wherein the first surface is at least generally parallel to the second surface, and the third surface is at least generally parallel to the fourth surface.21. The apparatus of claim 16 wherein the first surface is at least generally parallel to the third surface, and the second surface is at least generally parallel to the fourth surface, when the second part is engaged with the first part.22. The apparatus of claim 16 wherein at least a portion of the third and fourth surfaces of the second part are configured to be positioned between the first and second surfaces of the first part when the second part is engaged with the first part.23. The apparatus of claim 16 wherein at least a portion of the first and second surfaces of the first part are configured to be positioned between the third and fourth surfaces of the second part when the second part is engaged with the first part.24. The apparatus of claim 16 wherein the first part has two sets of associated flange portions, wherein the apparatus further comprises a third part configured to be engaged with one of the sets of associated flange portions of the first part, and wherein the third part is configured to be bonded to a third member.25. The apparatus of claim 16 wherein the first part has three sets of associated flange portions, and wherein the apparatus further comprises a third part and a fourth part, wherein each of the second, third and fourth parts are configured to be engaged with one of the sets of associated flange portions of the first part, and wherein the third part is configured to be bonded to the a third member, and the fourth part is configured to be bonded to a fourth member.26. The apparatus of claim 16 wherein the first part has four sets of associated flange portions, and wherein the apparatus further comprises a third part, a fourth part, and a fifth part, wherein each of the second, third, fourth, and fifth parts are configured to be engaged with one of the sets of associated flange portions of the first part, and wherein the third part is configured to be bonded to a third member, the fourth part is configured to be bonded to a fourth member, and the fifth part is configured to be bonded to a fifth member.27. The apparatus of claim 16 wherein the first protuberance is positioned on a distal end of the third flange portion and the second protuberance is positioned on a distal end of the fourth flange portion.28. The apparatus of claim 16 wherein the first recess is positioned at an intersection between the first surface and the first base portion and the second recess is positioned at an intersection between the second surface and the first base portion, wherein the first protuberance is positioned on a distal end of the third flange portion and the second protuberance is positioned on a distal end of the fourth flange portion, and wherein at least a portion of the third and fourth surfaces of the second part are configured to be positioned between the first and second surfaces of the first part when the second part is engaged with the first part.29. The apparatus of claim 16 wherein the first recess is positioned at an intersection between the first surface and the first base portion and the second recess is positioned at an intersection between the second surface and the first base portion, wherein the first protuberance is positioned on a distal end of the third flange portion and the second protuberance is positioned on a distal end of the fourth flange portion, and wherein at least a portion of the first and second surfaces of the first part are configured to be positioned between the third and fourth surfaces of the second part when the second part is engaged with the first part.30. The apparatus of claim 16 wherein the first and second surfaces are positioned at angles of from about 30 degrees to about 85 degrees relative to the first base surface.31. The apparatus of claim 16 wherein the first and second surfaces are positioned at angles of from about 60 degrees to about 85 degrees relative to the first base surface.32. The apparatus of claim 16 wherein the first and second surfaces are positioned at angles of from about 85 degrees to about 90 degrees relative to the first base surface.33. The apparatus of claim 16 wherein at least a portion of the first and second surfaces of the first part are configured to sandwich at least a portion of the second aircraft member.