Method of manufacturing curved composite structural elements
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B29C-065/00
B27N-003/10
B32B-009/04
출원번호
US-0119756
(2005-05-03)
등록번호
US-8632653
(2014-01-21)
발명자
/ 주소
Brown, Todd A.
Friddell, Stephen Douglas
Harris, Christopher G.
Modin, Andrew E.
출원인 / 주소
The Boeing Company
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
8인용 특허 :
43
초록▼
A method of manufacturing curved composite structural elements can include fabricating a web ply in a flat curve over a removable substrate and laying up the ply on a curved web surface of a manufacturing tool. The method also can include laying up a diagonal ply with fibers oriented at +/−45° from
A method of manufacturing curved composite structural elements can include fabricating a web ply in a flat curve over a removable substrate and laying up the ply on a curved web surface of a manufacturing tool. The method also can include laying up a diagonal ply with fibers oriented at +/−45° from the centerline of the web surface. The method further can include cutting a unidirectional composite tape into segments and laying up the tape segments to form a cross ply with a fiber orientation normal to the centerline of the web surface. One or both edges of the diagonal and cross plies may be folded over one or two sides of the manufacturing tool to form one or two flange surfaces. Additionally, a cap ply can be laid up on one or both flange surfaces using composite tape. The structural element layup can then be inspected and any excess composite material can be trimmed away.
대표청구항▼
1. A method comprising the steps of: forming a 0-degree, planar curved web ply of contiguous, adjoined fiber composite strips by placing the strips to lay contiguously adjoined on a flat surface and in the shape of a planar arc so that the fibers are in a 0-degree direction aligned with a full lengt
1. A method comprising the steps of: forming a 0-degree, planar curved web ply of contiguous, adjoined fiber composite strips by placing the strips to lay contiguously adjoined on a flat surface and in the shape of a planar arc so that the fibers are in a 0-degree direction aligned with a full length of a longitudinal centerline of the planar arc without distortion;trimming the web ply to conform to the shape of a perimeter of a planar curved web surface of a mandrel, said mandrel having first and second side cap surfaces which meet the web surface to form first and second corners respectively;laying up the web ply onto the web surface of the mandrel to have 0-degree fiber orientation substantially aligned with the full length of a longitudinal centerline of the web surface; andlaying up a 0-degree cap ply of fiber composite tape onto the first cap surface to form a splice with the web ply along the first corner of the mandrel, the tape comprising a plurality of tape fibers having 0-degree fiber orientation substantially aligned with a longitudinal centerline of the first cap surface, and the splice forming a continuous, substantially 0-degree ply lying across the web surface and the first cap surface. 2. The method of claim 1, further comprising laying up a 0-degree cap ply of fiber composite tape onto the second cap surface to form a second splice with the web ply along the second corner of the mandrel, the tape comprising a plurality of tape fibers having 0-degree fiber orientation substantially aligned with a longitudinal centerline of the second cap surface, and the second splice forming a continuous, substantially 0-degree ply lying across the web surface and the first and second cap surfaces. 3. The method of claim 2, further comprising forming a curved composite structural element by curing the resulting layup comprising the splices. 4. The method of claim 3, wherein the curved composite structural element is an aircraft structural member. 5. The method of claim 4, wherein the aircraft structural member is a floating frame. 6. The method of claim 3, wherein the curved composite structural element comprises a C-shaped cross section. 7. The method of claim 1, further comprising forming a curved composite structural element by curing the resulting layup comprising the splice. 8. The method of claim 7, wherein the curved composite structural element is an aircraft structural member. 9. The method of claim 8, wherein the aircraft structural member is a shear tie. 10. The method of claim 7, wherein the curved composite structural element comprises an L-shaped cross section. 11. The method of claim 1, wherein each strip is a slit composite tape. 12. The method of claim 1, wherein each strip is a prepreg tow. 13. The method of claim 1, wherein the web ply is formed on a removable substrate material. 14. The method of claim 13, further comprising removing the removable substrate material from the trimmed web ply subsequent to laying up the web ply on the web surface of the mandrel. 15. The method of claim 1, further comprising laying up a diagonal ply over the web surface of the mandrel. 16. The method of claim 15, further comprising laying up a cross ply over the web surface of the mandrel. 17. The method of claim 16, further comprising the steps of: sealing the resulting layup comprising the splice, the diagonal ply, and the cross ply within a vacuum bag to remove trapped air; andforming a curved composite structural element by curing the sealed layup. 18. The method of claim 17, further comprising inspecting the curved composite structural element for defects. 19. The method of claim 18, further comprising trimming the curved composite structural element. 20. The method of claim 1, further comprising the steps of: sealing the resulting layup comprising the splice within a vacuum bag to remove trapped air; andforming a curved composite structural element by curing the sealed layup. 21. The method of claim 20, further comprising inspecting the curved composite structural element for defects. 22. The method of claim 21, further comprising trimming the curved composite structural element. 23. The method of claim 1, further comprising the step of transferring the resulting layup comprising the splice onto a curved, concave manufacturing tool, the curved, concave manufacturing tool having a shape conforming to an external surface of the resulting layup. 24. The method of claim 11, wherein each strip is ⅛ inch wide. 25. The method of claim 12, wherein each strip is between 0.12 inch and 0.25 inch wide when flattened.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (43)
Pippel James J. (Rockford IL) Messner Bernd A. K. (Rockford IL), Adaptive control for tape laying head having natural path generation.
Benson, Vernon M.; Slack, Jason; Rosevear, Todd A.; Harvey, James L.; Roman, Mark; Olschewski, Timothy, Apparatus and methods for forming composite stiffeners and reinforcing structures.
Biornstad, Robert D.; Blankinship, Bruce C.; George, Terry J.; Ingram, William H., Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections.
Alenskis Brian A. (Bountiful UT) Geil Gerald L. (Diamond Bar CA) Gill Dee R. (Sandy UT) Moloney Brian N. (West Valley City UT), Filament winding system.
Maison, Serge; Meunier, Serge; Thibout, Cedric; Mouton, Luc; Payen, Herve; Vautey, Philippe; Coiffier-Colas, Carole; Delbez, Joel, Method for making parts in composite material with thermoplastic matrix.
Buge, Michel; Rambaud, Eric; Porte, Alain; Legeay, Bruno, Process for the production of a panel of composite material with stiffening strips and panel thus obtained.
Nithart Henri (8 rue de l\Eglantine Belfort FRX) Graftiaux Robert (8 rue de l\Eglantine 69500 Bron FRX), Taping machine for hot taping an electrical conductor.
Koerwien,Thomas; Bauer,Ernst Joachim; Filsinger,Juergen, Technical production method, tension module and sewing material holder for creating textile preforms for the production of fibre-reinforced plastic components.
Buttrick, James N.; Stewart, Dennis Wayne; Modin, Andrew E.; Banks, David Paul; Depase, Edoardo; Sanchez, Jesus, Method and apparatus for fabricating contoured laminate structures.
Downs, Roland Joseph; Adams, Christopher Michael; Holweger, Jon Michael, Systems and method for producing three-dimensional articles from flexible composite materials.
Downs, Roland Joseph; Adams, Christopher Michael; Holweger, Jon Michael; Hatcher, Wesley Edward; McDaniels, Keith Joel; Meldner, Heiner, Systems and method for producing three-dimensional articles from flexible composite materials.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.