Methods and apparatuses for providing corrosion protection to joined surfaces
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F16B-005/00
F16B-001/00
출원번호
US-0581553
(2017-04-28)
등록번호
US-9964131
(2018-05-08)
발명자
/ 주소
Mohaghegh, Mohssen
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
Coats & Bennett, PLLC
인용정보
피인용 횟수 :
0인용 특허 :
5
초록
Methods, systems and apparatuses are disclosed for joining assemblies, particularly joints and joining assemblies for co-joining composite components and metal components in a joining assembly, and inhibiting corrosion of metal components secured to composite component via a joining assembly.
대표청구항▼
1. A method for joining a composite component to a metal component via a joining assembly comprising: positioning a composite component in a first plane, said composite component comprising a composite component first end, and a composite component second end;substantially covering said composite co
1. A method for joining a composite component to a metal component via a joining assembly comprising: positioning a composite component in a first plane, said composite component comprising a composite component first end, and a composite component second end;substantially covering said composite component first end with a composite edge seal;positioning a metal component in said first plane or in a second plane, said metal component having a metal component first end and a metal component second end, wherein said second plane may be aligned with said first plane;positioning said composite component first end proximate to and at a predetermined distance from the metal component first end;positioning at least one joining assembly component proximate to the composite component first end and the metal component first end, said joining assembly dimensioned to join the composite component first end and the metal component first end, and said joining assembly component comprising a joining assembly component inner surface and a barrier extending from the joining assembly component inner surface, said barrier dimensioned to substantially separate the composite component first end from the metal component first end, said barrier comprising a barrier edge;substantially covering said barrier edge with a barrier edge seal;fastening the composite component first end to the joining assembly; andfastening the metal component first end to the joining assembly at a predetermined distance from the composite component first end to join the composite component to the metal component via the joining assembly. 2. The method of claim 1, wherein, after the step of fastening the composite component first end to the joining assembly component further comprising: establishing a first chamber, said first chamber bounded by the barrier, the joining assembly component inner surface and a composite component edge seal, said barrier edge positioned proximate to the joining assembly component inner surface; andestablishing a second chamber, said second chamber bounded by the barrier, the joining assembly component inner surface and the metal component first end, said barrier edge positioned proximate to the joining assembly component inner surface. 3. The method of claim 1, wherein, in the step of positioning at least one joining assembly component proximate to the composite component first end and the metal component first end, said joining assembly comprises a joining assembly first plate and a joining assembly second plate. 4. The method of claim 3, wherein, in the step of positioning at least one joining assembly component proximate to the composite component first end and the metal component first end, the joining assembly first plate and the joining assembly second plate are joined together to retain the composite component first end and the metal component first end between the joining assembly first plate and joining assembly second plate. 5. The method of claim 4, wherein, in the step of positioning at least one joining assembly component proximate to the composite component first end and the metal component first end, the joining assembly first plate and the joining assembly second plate comprise titanium or a titanium alloy. 6. The method of claim 1, wherein, in the step positioning a composite component in a first plane, the composite component comprises a carbon fiber reinforced polymer. 7. The method of claim 1, wherein, in the step positioning a metal component in said second plane, the metal component comprises aluminum or an aluminum alloy. 8. A method for joining a composite component to a metal component via a joining assembly comprising: positioning a composite component in a first plane, said composite component comprising a composite component first end, and a composite component second end;substantially covering said composite component first end with a composite edge seal;positioning a metal component in said first plane or in a second plane, said metal component having a metal component first end and a metal component second end, wherein said second plane may be aligned with said first plane;positioning said composite component first end proximate to and at a predetermined distance from the metal component first end;positioning a joining assembly first plate and a joining assembly second plate proximate to the composite component first end and the metal component first end, said joining assembly first plate and said joining assembly second plate dimensioned to join the composite component first end and the metal component first end, and said joining assembly first plate comprising a joining assembly first plate inner surface, said joining assembly second plate comprising a joining assembly second plate inner surface, and a barrier extending from at least one of the joining assembly first plate inner surface and the joining assembly second plate inner surface, said barrier dimensioned to substantially separate the composite component first end from the metal component first end, said barrier comprising a barrier edge;substantially covering said barrier edge with a barrier edge seal;fastening the composite component first end to the joining assembly; andfastening the metal component first end to the joining assembly at a predetermined distance from the composite component first end;wherein moisture is inhibited from contacting the composite component first end. 9. A joining assembly for joining a composite component to a metal component comprising: a composite component configured in a first plane, said composite component comprising: a composite component first end, and a composite component second end; anda composite edge seal configured to substantially cover the composite component first end;a metal component configured in the first plane or in a second plane, said metal component comprising: a metal component first end and a metal component second end, wherein said second plane may be aligned with said first plane; said metal component first end positioned proximate to and at a predetermined distance from the composite component first end;a joining assembly positioned proximate to the composite component first end and the metal component first end, said joining assembly dimensioned to join the composite component first end and the metal component first end, and said joining assembly comprising a barrier dimensioned to substantially separate the composite component first end from the metal component first end, said barrier comprising a barrier edge; anda barrier edge seal configured to substantially cover the barrier edge. 10. The joining assembly of claim 9, wherein the composite component comprises a fiber-reinforced polymer. 11. The joining assembly of claim 9, wherein the metal component comprises aluminum or an aluminum alloy. 12. The joining assembly of claim 9, wherein the barrier comprises titanium or a titanium alloy. 13. The joining assembly of claim 9, wherein the joining assembly comprises titanium or a titanium alloy. 14. The joining assembly of claim 9, wherein the joining assembly is configured such that moisture is inhibited from contacting the composite component first end. 15. A joining assembly for an aircraft comprising the joining assembly of claim 9. 16. A vehicle comprising the joining assembly of claim 9, said vehicle selected from the group consisting of: a manned aircraft, an unmanned aircraft, a manned spacecraft, an unmanned spacecraft, a manned rotorcraft, an unmanned rotorcraft, a satellite, a rocket, a manned terrestrial vehicle, an unmanned terrestrial vehicle, a manned surface water borne vehicle, an unmanned surface water borne vehicle, a manned sub-surface water borne vehicle, an unmanned sub-surface water borne vehicle, and combinations thereof. 17. The joining assembly of claim 10, wherein the composite component comprises a fiber-containing epoxy resin. 18. The joining assembly of claim 9, further comprising a joining assembly first plate and a joining assembly second plate, said joining assembly first plate and joining assembly second plate configured to retain the composite component first end and the metal component first end between the joining assembly first plate and the joining assembly second plate. 19. The joining assembly of claim 9, wherein the composite component comprises a carbon fiber-reinforced polymer. 20. The joining assembly of claim 16, wherein the barrier is integral with at least one of a joining assembly first plate and a joining assembly second plate.
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이 특허에 인용된 특허 (5)
Kismarton, Max U.; Westre, Willard N., Composite wing-body joint.
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