Joints between a composite skin and a load-bearing component and methods of forming same
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/12
B29C-065/56
B29C-065/00
B64C-001/00
B29L-031/30
B29K-105/08
B29K-307/04
출원번호
US-0209129
(2016-07-13)
등록번호
US-10029777
(2018-07-24)
발명자
/ 주소
Rosman, Richard R.
Dopker, Bernhard
Chan, Wallace Chi-Hua
출원인 / 주소
The Boeing Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
0인용 특허 :
13
초록▼
A method of forming a direct bearing joint includes coupling a first load-bearing structure to a second load-bearing structure. The second load-bearing structure includes a first structural feature comprising a first arcuate shape. The method also includes coupling a composite skin including a secon
A method of forming a direct bearing joint includes coupling a first load-bearing structure to a second load-bearing structure. The second load-bearing structure includes a first structural feature comprising a first arcuate shape. The method also includes coupling a composite skin including a second structural feature comprising a second arcuate shape to the second load-bearing structure. The composite skin is coupled to the second load-bearing structure such that the first and second structural features are mated against each other to facilitate distributing compressive loads from the second load-bearing structure into the composite skin.
대표청구항▼
1. A method of forming a direct bearing joint, the method comprising: coupling a first load-bearing structure to a second load-bearing structure, wherein the second load-bearing structure comprises a first structural feature, the first structural feature comprising a first arcuate shape; andcoupling
1. A method of forming a direct bearing joint, the method comprising: coupling a first load-bearing structure to a second load-bearing structure, wherein the second load-bearing structure comprises a first structural feature, the first structural feature comprising a first arcuate shape; andcoupling a composite skin, which comprises a second structural feature, the second structural feature comprising a second arcuate shape, to the second load-bearing structure such that the first structural feature and the second structural feature are mated against each other to facilitate distributing compressive loads from the second load-bearing structure into the composite skin, wherein the first structural feature is positioned between the first load-bearing structure and the composite skin. 2. The method in accordance with claim 1, wherein coupling the first load-bearing structure to the second load-bearing structure comprises coupling one of a longeron, a keel beam, or a wing spar of an aircraft to the second load-bearing structure. 3. The method in accordance with claim 2, wherein coupling the first load-bearing structure to the second load-bearing structure comprises coupling one of the longeron, the keel beam, or the wing spar of the aircraft to a bearing plate. 4. The method in accordance with claim 1, further comprising coupling the composite skin between a bulkhead and a structural flange of the second load-bearing structure. 5. The method in accordance with claim 1, wherein: the first structural feature comprises a convex platform edge;the second structural feature comprises a concave cutout; andcoupling the composite skin to the second load-bearing structure comprises coupling the concave cutout to the convex platform edge. 6. The method in accordance with claim 5, wherein coupling the composite skin, which comprises the concave cutout, to the second load-bearing structure further comprises mating the convex platform edge of the second load-bearing structure in continuous direct contact against the concave cutout of the composite skin. 7. The method in accordance with claim 1, further comprising coupling the first load-bearing structure, the second load-bearing structure, and the composite skin together using a plurality of fasteners such that a first load path is defined through the first structural feature and the second structural feature and such that a second load path is defined through the plurality of fasteners. 8. The method in accordance with claim 1, wherein coupling the first load-bearing structure to the second load-bearing structure comprises coupling the first load-bearing structure, which comprises a first portion and a second portion, perpendicular to the first portion, to the second load-bearing structure. 9. A direct bearing joint comprising: a first load-bearing structure, comprising a first portion and a second portion, the second portion coupled to and extending from the first portion such that the first portion is substantially perpendicular to the second portion;a second load-bearing structure, coupled to the first load-bearing structure and comprising a first structural feature comprising a first arcuate shape; anda composite skin, coupled to the second load-bearing structure such that the first structural feature is positioned between the first load-bearing structure and the composite skin, the composite skin comprising a second structural feature comprising a second arcuate shape, the second structural feature operable to mate against the first structural feature to facilitate distributing compressive loads from the second load-bearing structure into the composite skin. 10. The direct bearing joint in accordance with claim 9, wherein the first structural feature is a convex platform and the second structural feature is a complementary concave cutout. 11. The direct bearing joint in accordance with claim 9, wherein the first structural feature comprises a first edge and the second structural feature comprises a second edge that is shaped to mate against the first edge. 12. The direct bearing joint in accordance with claim 9, wherein the first load-bearing structure is one of a wheel-well longeron, a keel beam, or a wing rear spar frame of an aircraft. 13. The direct bearing joint in accordance with claim 12, wherein the second load-bearing structure is a bearing plate, coupled to one of the wheel-well longeron, the keel beam, or the wing rear spar frame of the aircraft. 14. The direct bearing joint in accordance with claim 9, further comprising a plurality of fasteners, operable to couple the composite skin to the first load-bearing structure and to the second load-bearing structure, such that a first load path is defined through the first structural feature and the second structural feature, and such that a second load path is defined through the plurality of fasteners. 15. The direct bearing joint in accordance with claim 9, further comprising a bulkhead, wherein the second load-bearing structure further comprises an extension flange, and the composite skin is coupled between the extension flange and the bulkhead. 16. The direct bearing joint in accordance with claim 15, wherein the second load-bearing structure comprises a first inner surface, coupled in a mating relationship with an outer surface of the bulkhead, and the composite skin comprises a second inner surface, coupled in a mating relationship with the outer surface of the bulkhead such that the first inner surface and the second inner surface are substantially flush against each other. 17. An aircraft comprising a direct bearing joint, the aircraft comprising: a first load-bearing structure;a bulkhead;a second load-bearing structure, coupled between the bulkhead and the first load-bearing structure and comprising a first structural feature that comprises a first arcuate shape; anda composite skin, coupled to the second load-bearing structure such that the first structural feature is positioned between the first load-bearing structure and the composite skin, the composite skin comprising a second structural feature that comprises a second arcuate shape, wherein the second structural feature is operable to mate against the first structural feature to facilitate distributing compressive loads from the second load-bearing structure into the composite skin. 18. The aircraft in accordance with claim 17, wherein the first structural feature comprises a first edge, and the second structural feature comprises a second edge that is shaped to mate against the first edge. 19. The aircraft in accordance with claim 17, wherein the first load-bearing structure is one of a wheel-well longeron, a keel beam, or a wing rear spar frame, and wherein the second load-bearing structure is a bearing plate. 20. The aircraft in accordance with claim 17 further comprising a plurality of fasteners operable to couple the composite skin to the first load-bearing structure and the second load-bearing structure, such that a first load path is defined through the first and second structural features, and such that a second load path is defined through the plurality of fasteners.
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