[특허]Composite tube having cobonded end fittings and method of making same

The Boeing Company

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특허 상세정보

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Composite tube having cobonded end fittings and method of making same

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B32B-037/00
미국특허분류(USC)	156/172; 156/173; 156/175; 156/185; 156/187; 156/188; 156/192
출원번호	US-0607546 (2006-12-02)
등록번호	US-8414724 (2013-04-09)
발명자 / 주소	Schnelz, James R.
출원인 / 주소	The Boeing Company
대리인 / 주소	Yee & Associates, P.C.
인용정보	피인용 횟수 : 4 인용 특허 : 32

초록

A structural member such as a strut includes a composite material tube having metal end fittings that are attached to the tube by co-bonded, double shear joints. The double shear bond joint construction reduces the residual stress on the bonds that result from mismatch of the coefficients of thermal expansion of the composite tube and the metal end fittings. The ends of the fittings that are bonded to the tube may include a stepped profile that functions to limit the peak stresses in the bonds.

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1. A method of making a structural member, comprising the steps of: forming an inner composite tube wall portion having a first end and a second end comprising a lay-up of uncured composite material, forming comprising wrapping a plurality of uncured plies of a fiber reinforced polymer material onto a mandrel to form, a number of the plurality of uncured plies being wrapped one revolution or less around the mandrel;coupling a first fitting over at least a portion of the first end of the inner composite tube wall portion and curing said inner composite tube wall portion with said fitting in place;forming an outer composite tube wall portion comprising a second lay-up of uncured composite material over at least a portion of the inner tube wall portion and the first fitting following the coupling of the first fitting over at least a portion of the first end of the inner composite tube wall portion and curing said inner composite tube wall portion with said fitting in place; and,co-bonding the inner composite tube wall portion, the outer composite tube wall portion, and the first fitting by curing said second lay-up. 2. The method of claim 1, wherein forming the inner composite tube wall portion further comprises compacting the lay-up to form a compacted lay-up. 3. The method of claim 2, wherein forming the inner composite tube wall portion further comprises placing a female mold over the compacted lay-up. 4. The method of claim 3, wherein forming the inner composite tube wall portion further comprises sealing the female mold to the compacted lay-up to form a chamber therebetween. 5. The method of claim 4, wherein forming the inner composite tube wall portion further comprises evacuating the chamber. 6. The method of claim 1, further comprising the steps of: inserting the mandrel into a mandrel mold,expanding the mandrel within the mold to form the mandrel into a desired mandrel shape; and,removing the mold. 7. The method of claim 6, further comprising the steps of: placing a second fitting over at least a portion of the second end of the inner tube wall portion, andindexing a rotational position of the first fitting relative to a rotational position of the second fitting using indexing marks on the mandrel. 8. The method of claim 6, wherein expanding the mandrel is performed by inflating the mandrel. 9. The method of claim 1, wherein forming the outer composite tube wall portion includes: laying a number of plies of composite material over the inner tube wall and over the fitting,compacting the number of plies to form a number of compacted plies; and,curing the number of compacted plies. 10. The method of claim 1, wherein said structural member comprises an aircraft strut. 11. The method of claim 1, wherein said fitting forms a first bond joint with the inner tube wall portion, and a second bond joint with the outer tube wall portion. 12. The method of claim 1, wherein the fitting includes a cylindrical wall having a tapered thickness, said tapered thickness decreasing in a direction toward said tube wall portions, and, the inner and outer tube wall portions on either side of said fitting each have a taper complementing the tapered thickness of the fitting. 13. The method of claim 1, wherein the number of the plurality of uncured plies comprise hoop plies. 14. The method of claim 1, wherein the plurality of uncured plies are configured to allow reinforcing fibers of the plurality of uncured plies to move radially during a subsequent compaction of the lay-up. 15. A method of making a composite aircraft strut having a metal fitting, comprising the steps of: forming a first lay-up of uncured composite material defining an inner tube wall portion having a first end and a second end, forming comprising wrapping a plurality of uncured plies of a fiber reinforced polymer material onto a mandrel, a number of the plurality of uncured plies being wrapped one revolution or less around the mandrel;coupling at least a section of a metal fitting over at least a portion of the first end of the inner tube wall portion to create a fitting section and curing said inner tube wall with said metal fitting in place;forming a second lay-up of composite material over the first lay-up and at least a portion of the fitting section, the second lay-up defining an outer tube wall portion covering the inner tube wall portion and the fitting section; and,co-bonding the inner tube wall portion, the outer tube wall portion, and the fitting section by curing said second lay-up. 16. The method of claim 15, further comprising the steps of: compacting the plies laid up on the mandrel. 17. The method of claim 15, further comprising the steps of: inserting the mandrel into a mandrel mold,expanding the mandrel within the mold to form the mandrel into a desired mandrel shape; and,removing the mandrel mold before the plies are laid up on the mandrel. 18. The method of claim 15, wherein: forming the second lay-up of composite material over the first lay-up and at least a portion of the fitting section further includes wrapping uncured plies of a fiber reinforced polymer material over the first lay-up and over at least a portion of the fitting section. 19. The method of claim 18, wherein forming the second lay-up of composite material over the first lay-up and at least a portion of the fitting section and further wrapping uncured plies of the fiber reinforced polymer material over the first lay-up and over at least a portion of the fitting section, still further comprises compacting the uncured plies. 20. The method of claim 15, wherein the number of the plurality of uncured plies comprise hoop plies. 21. The method of claim 15, wherein the plurality of uncured plies are configured to allow reinforcing fibers of the plurality of uncured plies to move radially during a subsequent compaction of the first lay-up. 22. A method of making a structural member, comprising the steps of: forming an inner composite tube wall portion comprising a lay-up of uncured composite material, forming comprising wrapping a plurality of uncured plies of a fiber reinforced polymer material onto a mandrel, a number of the plurality of uncured plies being wrapped one revolution or less around the mandrel;coupling a fitting over at least a portion of an end of the inner composite tube wall portion and curing said inner composite tube wall portion with said fitting in place;forming an outer composite tube wall portion comprising a second lay-up of uncured composite material over at least a portion of the inner tube wall portion and the fitting following curing of said inner composite tube and said fitting;co-bonding the inner composite tube wall portion, the outer composite tube wall portion, and the fitting to form a joint by curing said second lay-up; andwherein the fitting includes a cylindrical wall having a tapered thickness, said tapered thickness decreasing in a direction toward said tube wall portions, and, the inner and outer tube wall portions on either side of said fitting each have a taper complementing the tapered thickness of the fitting. 23. The method of claim 22, wherein the step of forming the inner composite tube wall portion further comprises compacting the lay-up of uncured composite material. 24. The method of claim 23, wherein the compacting further comprises placing a female mold over the lay-up of uncured composite material. 25. The method of claim 22, wherein, before the lay-up of uncured composite material is formed over the mandrel, the mandrel is first inserted into a mandrel mold, expanded within the mold to form the mandrel into a desired mandrel shape, and then removed from the mold. 26. The method of claim 22, wherein the step of forming the outer composite tube wall portion further comprises: laying plies of composite material over the inner tube wall and over the fitting,compacting the plies to form a lay-up of compacted plies, and,curing the lay-up of compacted plies. 27. The method of claim 22, wherein said structural member comprises an aircraft strut. 28. The method of claim 22, wherein the number of the plurality of uncured plies comprise hoop plies. 29. The method of claim 22, wherein the plurality of uncured plies are configured to allow reinforcing fibers of the plurality of uncured plies to move radially during a subsequent compaction of the lay-up.

이 특허에 인용된 특허 (32)

이 특허를 인용한 특허 피인용횟수: 4

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Composite tube having cobonded end fittings and method of making same

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Composite tube having cobonded end fittings and method of making same

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