IPC분류정보
| 국가/구분 |
United States(US) Patent
등록
|
| 국제특허분류(IPC7판) |
|
| 출원번호 |
UP-0888565
(2004-07-08)
|
| 등록번호 |
US-7753312
(2010-08-02)
|
| 우선권정보 |
DE-103 30 708(2003-07-08) |
|
발명자
/ 주소 |
- Schmidt, Hans-Juergen
- Vichniakov, Alexei
|
| 출원인 / 주소 |
|
| 대리인 / 주소 |
|
| 인용정보 |
피인용 횟수 :
0 인용 특허 :
64 |
초록
▼
A fiber reinforced strip is adhesively bonded to an outwardly facing surface of a reinforcing frame and to an inwardly facing outer skin surface. Such a strip position reduces crack propagation in a lightweight structure particularly in the outer skin adhesively bonded to the reinforcing frame throu
A fiber reinforced strip is adhesively bonded to an outwardly facing surface of a reinforcing frame and to an inwardly facing outer skin surface. Such a strip position reduces crack propagation in a lightweight structure particularly in the outer skin adhesively bonded to the reinforcing frame through the strip. For this purpose the fiber reinforced strip is interposed between the outer skin and the frame and adhesively bonded to the outer skin and to the frame. The strip has reinforcing fibers extending in parallel to each other or the reinforcing fibers are woven into a fabric embedded in a synthetic adhesive bonding material. The embedding of the parallel fibers or of the fiber fabric in the bonding material is performed either prior to the bonding or during the bonding of the strip to the outer skin and to the reinforcing frame.
대표청구항
▼
What is claimed is: 1. A lightweight structure comprising an outer sheet metal material skin, a reinforcing frame including ribs and stringers, said ribs and stringers having skin facing surfaces having a width within the range of 10 to 80 mm, said outer sheet metal material skin comprising a sheet
What is claimed is: 1. A lightweight structure comprising an outer sheet metal material skin, a reinforcing frame including ribs and stringers, said ribs and stringers having skin facing surfaces having a width within the range of 10 to 80 mm, said outer sheet metal material skin comprising a sheet metal material wherein cracks can occur, wherein said sheet metal material is selected from the group consisting of aluminum alloy, magnesium alloy, titanium alloy and fiber metal laminates, and at least one fiber reinforced crack propagation retarding strip interposed between said outer sheet metal material skin and said skin facing surfaces of any one of said ribs and stringers forming said reinforcing frame, said at least one fiber reinforced crack propagation retarding strip having a strip width within said range of 10 to 80 mm of said skin facing surfaces, and an adhesive bond between said at least one fiber reinforced crack propagation retarding strip and said outer sheet metal material skin and a further adhesive bond between a respective skin facing surface of any one of said ribs and stringers forming said reinforcing frame and said at least one fiber reinforced crack propagation retarding strip. 2. The lightweight structure of claim 1, wherein said at least one fiber reinforced crack propagation retarding strip comprises fibers embedded in a matrix, said fibers extending in parallel to each other. 3. The lightweight structure of claim 1, wherein said at least one fiber reinforced crack propagation retarding strip comprises fibers woven into a fabric embedded in a matrix, said fibers crossing each other. 4. The lightweight structure of claim 1, wherein said at least one fiber reinforced crack propagation retarding strip comprises fibers embedded in a matrix material having a damage tolerant characteristic. 5. The lightweight structure of claim 4, wherein said fibers in said at least one fiber reinforced crack propagation retarding strip are selected from the group consisting of glass fibers, carbon fibers, polyaromatic amide fibers, aluminum oxide fibers, silicon carbide fibers and basalt fibers. 6. The lightweight structure of claim 4, wherein said fibers in said at least one fiber reinforced crack propagation retarding strip are metal wires selected from the group of aluminum wires, titanium wires, magnesium wires, and wires of alloys of these metals including aluminum lithium alloy wires. 7. The lightweight structure of claim 6, wherein said metal wires have a diameter within the range of 0.001 mm to 0.3 mm. 8. The lightweight structure of claim 4, wherein said fibers in said at least one fiber reinforced crack propagation retarding strip have a diameter within the range of 0.001 mm to 0.3 mm. 9. The lightweight structure of claim 1, wherein said at least one fiber reinforced crack propagation retarding strip has a strip thickness within the range of 0.05 mm to 0.3 mm following adhesive bonding. 10. The lightweight structure of claim 1, wherein said at least one fiber reinforced crack propagation retarding strip comprises fibers having a length of at least 10 mm. 11. The lightweight structure of claim 1, wherein said sheet metal material forming said outer skin is a monolithic single ply sheet metal. 12. The lightweight structure of claim 1, wherein said sheet metal material of said aluminum alloy is an aluminum lithium alloy. 13. The lightweight structure of claim 12, wherein said aluminum lithium alloy comprises 1% to 3% by weight of lithium. 14. An aircraft fuselage structure comprising: an outer skin comprising at least one sheet metal layer of a metal material selected from the group consisting of aluminum alloys, magnesium alloys and titanium alloys; a structural frame comprising plural ribs that are spaced apart from one another and plural stringers that are spaced apart from one another, wherein said stringers extend crosswise relative to said ribs with open fields to between and bounded by said ribs and said stringers to form a grid pattern of said structural frame, wherein said ribs and said stringers have outer surfaces thereof facing an inner surface of said outer skin, and wherein said outer surfaces of said ribs and said stringers each respectively is have a width within a range from 10 mm to 80 mm; and fiber reinforced composite strips of a fiber reinforced composite material arranged in a grid pattern between and adhesively bonded to said inner surface of said outer skin and said outer surfaces of said ribs and said stringers, wherein said fiber reinforced composite strips each respectively have a width within a range from 10 mm to 80 mm. 15. The aircraft fuselage structure according to claim 14, wherein said fiber reinforced composite strips are arranged only in said grid pattern along all of said outer surfaces of all of said ribs and said stringers, and no fiber reinforced composite material is arranged on areas of said inner surface of said outer skin in said open fields of said structural frame. 16. The aircraft fuselage structure according to claim 14, wherein said respective width of each respective one of said fiber reinforced composite strips respectively corresponds to said respective width of said respective outer surface of a respective one of said ribs and said stringers to which said respective fiber reinforced composite strip is adhesively bonded. 17. The aircraft fuselage structure according to claim 14, wherein said outer skin is a monolithic single-ply sheet metal skin that consists of one said sheet metal layer. 18. The aircraft fuselage structure according to claim 14, wherein said at least one sheet metal layer comprises plural sheet metal layers, and said outer skin is a multi-ply laminate comprising said plural sheet metal layers laminated to one another. 19. The aircraft fuselage structure according to claim 18, wherein said multi-ply laminate further comprises at least one fiber reinforced composite layer laminated between adjacent ones of said sheet metal layers. 20. The aircraft fuselage structure according to claim 14, wherein said fiber reinforced composite strips each respectively comprise fibers having a length of at least 10 mm embedded in a matrix material that adhesively bonds said fiber reinforced composite strips to said inner surface of said outer skin and to said outer surfaces of said ribs and said stringers.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.