Apparatuses and methods for joining composite members and other structural members in aircraft wing boxes and other structures
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0504539
(2009-07-16)
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등록번호 |
US-8104714
(2012-01-31)
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발명자
/ 주소 |
- Brown, Stephen T.
- Kismarton, Max U.
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
5 인용 특허 :
2 |
초록
▼
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 an
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 angle 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.
대표청구항
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1. An aircraft wing box structure comprising: a front wing spar having a front spar web, wherein the front spar web is constructed from composite materials;a rear wing spar having a rear spar web, wherein the rear spar web is constructed from composite materials;a plurality of wing ribs extending be
1. An aircraft wing box structure comprising: a front wing spar having a front spar web, wherein the front spar web is constructed from composite materials;a rear wing spar having a rear spar web, wherein the rear spar web is constructed from composite materials;a plurality of wing ribs extending between the front wing spar and the rear wing spar, wherein each wing rib has a corresponding rib web constructed from composite materials, wherein each rib web has a front portion and a rear portion, and wherein each rib web is fixedly attached to the front spar web by:a first metallic joining member having a first base portion and a first upstanding leg portion, wherein the first base portion includes a first surface portion structurally bonded to the front spar web, and wherein the first upstanding leg portion includes a second surface portion structurally bonded to the front portion of the rib web; anda second metallic joining member having a second base portion and a second upstanding leg portion, wherein the second upstanding leg portion includes a third surface portion structurally bonded to the front portion of the rib web opposite the first upstanding leg of the first metallic joining member, 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 front spar web. 2. The aircraft wing box structure of claim 1 wherein the front and rear spar webs are generally flat, and wherein each of the front and rear spar webs has a tapered upper edge portion extending in a first direction and a tapered lower edge portion extending in a second direction opposite to the first direction. 3. The aircraft wing box structure of claim 1 wherein one side of each rib web is at least generally flat and the other side of each rib web is convex. 4. The aircraft wing box structure of claim 1 wherein each rib web includes a core portion sandwiched between a first face sheet and a second face sheet. 5. The aircraft wing box structure of claim 1 wherein the front spar web includes a first core portion sandwiched between a first face sheet and a second face sheet, and the rear spar web includes a second core portion sandwiched between a third face sheet and a fourth face sheet. 6. The aircraft wing box structure of claim 1 wherein each rib web is further fixedly attached to the rear spar web by: a third metallic joining member having a fourth surface portion structurally bonded to the rear spar web and a fifth surface portion structurally bonded to the rear portion of the rib web. 7. The aircraft wing box structure of claim 1 wherein each rib web further includes a fourth surface portion opposite a fifth surface portion, wherein the second surface portion is structurally bonded to the fourth surface portion of the rib web, and wherein the third surface portion is structurally bonded to the fifth surface portion of the rib web. 8. An aircraft wing structure comprising: a first composite wing spar;a second composite wing spar;a composite rib extending at least partially between the first and second composite wing spars, the composite rib having a front edge portion positioned proximate to the first composite wing spar and a rear edge portion positioned proximate to the second composite wing spar, wherein the front edge portion includes a first side facing opposite a second side;first means for fixedly attaching the first side of the front edge portion of the composite rib to the first composite wing spar in the absence of any structural fasteners extending through the first composite wing spar, wherein the first means includes a first base portion bonded to the first composite wing spar; andsecond means for fixedly attaching the second side of the front edge portion of the composite rib to the first composite wing spar in the absence of any structural fasteners extending through the first composite wing spar, wherein the second means includes a second base portion, and wherein the first base portion is sandwiched between the second base portion and the first composite wing spar. 9. The aircraft wing structure of claim 8 wherein the front edge portion of the composite wing rib is tapered, and wherein the first and second means include means for receiving the tapered front edge portion. 10. The aircraft wing structure of claim 8 wherein the composite rib further includes an upper edge portion and a lower edge portion, and wherein the aircraft wing structure further comprises: a first composite skin panel covering at least a portion of the first composite wing spar and the second composite wing spar proximate to the upper edge portion of the composite rib;a second composite skin panel covering at least a portion of the first composite wing spar and the second composite wing spar proximate to the lower edge portion of the composite rib;means for fixedly attaching the upper edge portion of the composite rib to the first composite skin panel in the absence of any structural fasteners extending through the composite rib; andmeans for means for fixedly attaching the lower edge portion of the composite rib to the second composite skin panel in the absence of any structural fasteners extending through the composite rib. 11. The aircraft wing structure of claim 8 wherein the composite rib further includes a core portion sandwiched between a first face sheet and a second face sheet, wherein the first and second face sheets are bonded together along the front edge portion of the composite wing rib to form a tapered front edge portion, wherein the first and second face sheets are bonded together along the rear edge portion of the composite wing rib to form a tapered rear edge portion, wherein the first and second face sheets are bonded together along an upper edge portion of the composite wing rib to form a tapered upper edge portion, wherein the first and second face sheets are bonded together along a lower edge portion of the composite wing rib to form a tapered lower edge portion, and wherein the aircraft wing structure further comprises: a first composite skin panel covering at least a portion of the first composite wing spar and the second composite wing spar proximate to the tapered upper edge portion of the composite rib;a second composite skin panel covering at least a portion of the first composite wing spar and the second composite wing spar proximate to the tapered lower edge portion of the composite rib;means for fixedly attaching the tapered upper edge portion of the composite rib to the first composite skin panel in the absence of any structural fasteners extending through the composite rib; andmeans for means for fixedly attaching the tapered lower edge portion of the composite rib to the second composite skin panel in the absence of any structural fasteners extending through the composite rib. 12. An aircraft wing box structure comprising: a wing spar having a spar web;a wing rib having a rib web formed by a core portion sandwiched between a first facesheet and a second facesheet, wherein the first and second facesheets are joined together along an outer boundary to form a tapered edge portion that at least approximately abuts the spar web;a first metallic joining member having a first base portion positioned adjacent to the spar web and a first upstanding leg portion positioned adjacent to the first facesheet of the rib web;a second metallic joining member having a second base portion positioned adjacent to the spar web and a second upstanding leg portion positioned adjacent to the second facesheet of the rib web, wherein the outer boundary of the tapered edge portion is sandwiched between the first upstanding leg portion and the second upstanding leg portion;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 facesheet of the rib web; anda second portion of adhesive forming a second structural bond between the second upstanding leg portion of the second metallic joining member and the second facesheet of the rib web, 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 spar web. 13. The aircraft wing box structure of claim 12 wherein the spar web is constructed from composite materials. 14. The aircraft wing box structure of claim 12, 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 spar web; anda 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. 15. The aircraft wing box structure of claim 12 wherein the tapered edge portion of the rib web 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. 16. The aircraft wing box structure of claim 12 wherein the spar web includes a second core portion sandwiched between a third facesheet and a fourth facesheet. 17. The aircraft wing box structure of claim 12 wherein the wing spar is a first wing spar having a first spar web, wherein the tapered edge portion of the rib web is a first tapered edge portion and the rib web further includes a second tapered edge portion opposite the first tapered edge portion, and wherein the aircraft wing box structure further comprises: a second wing spar having a second spar web, wherein the second tapered edge portion of the wing rib at least approximately abuts the second spar web;a third metallic joining member having a third base portion positioned adjacent to the second spar web and a third upstanding leg portion positioned adjacent to the first facesheet of the rib web;a fourth metallic joining member having a fourth base portion positioned adjacent to the second spar web and a fourth upstanding leg portion positioned adjacent to the second facesheet of the rib web, wherein the second tapered edge portion is sandwiched between the third upstanding leg portion and the fourth upstanding leg portion;a third portion of adhesive forming a third structural bond between the third upstanding leg portion of the third metallic joining member and the first facesheet of the rib web; anda fourth portion of adhesive forming a fourth structural bond between the fourth upstanding leg portion of the fourth metallic joining member and the second facesheet of the rib web. 18. The aircraft wing box structure of claim 17 wherein the wing rib further includes an upper edge portion and a lower edge portion, and wherein the aircraft wing box structure further comprises: a first composite skin panel covering at least a portion of the first wing spar and the second wing spar proximate the upper edge portion of the wing rib;a second composite skin panel covering at least a portion of the first wing spar and the second wing spar proximate the lower edge portion of the wing rib;means for fixedly attaching the upper edge portion of the wing rib to the first composite skin panel in the absence of any structural fasteners extending through the wing rib; andmeans for means for fixedly attaching the lower edge portion of the wing rib to the second composite skin panel in the absence of any structural fasteners extending through the wing rib.
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Christman, David B.; Roeseler, William G., Apparatuses and methods for joining structural members, such as composite structural members.
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Lackman Leslie M. (Tarzana CA) Hill John A. (Lawndale CA), Reinforced composite structure and method of fabrication thereof.
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Gray, Ian L., Elongate composite structural members and improvements therein.
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