Method for making parts in composite material with thermoplastic matrix
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B29C-065/40
B29C-070/32
B29C-051/02
B29C-053/04
출원번호
US-0462748
(2000-05-03)
우선권정보
FR-0009265 (1997-07-22)
국제출원번호
PCT/FR98/01584
(1998-07-20)
국제공개번호
WO99/04952
(1999-02-04)
발명자
/ 주소
Maison, Serge
Meunier, Serge
Thibout, Cedric
Mouton, Luc
Payen, Herve
Vautey, Philippe
Coiffier-Colas, Carole
Delbez, Joel
출원인 / 주소
Aerospatiale Societe Nationale Industrielle
대리인 / 주소
Thelen Reid & Priest LLP
인용정보
피인용 횟수 :
78인용 특허 :
9
초록▼
A process is proposed for the fabrication of parts with large dimensions formed of a skin (10) and stiffeners (12, 16) such as aircraft fuselage segments made of a composite material with a thermoplastic matrix. After stiffeners have been made separately by lay-up, consolidation and shaping, these s
A process is proposed for the fabrication of parts with large dimensions formed of a skin (10) and stiffeners (12, 16) such as aircraft fuselage segments made of a composite material with a thermoplastic matrix. After stiffeners have been made separately by lay-up, consolidation and shaping, these stiffeners are placed on a tooling (23) and the skin (10) is simultaneously fabricated and assembled to the stiffeners (12, 16) by diffusion welding. More precisely, the skin (10) is laid up and continuously consolidated by the lay-up head (36) such that the required part is obtained directly.
대표청구항▼
1. Fabrication process for parts from a composite material comprising a skin and stiffeners, the process comprising: separately fabricating stiffeners by lay-up, consolidation and shaping, starting from a strip of long fibers impregnated with thermoplastic resin; placing the stiffeners on a tool
1. Fabrication process for parts from a composite material comprising a skin and stiffeners, the process comprising: separately fabricating stiffeners by lay-up, consolidation and shaping, starting from a strip of long fibers impregnated with thermoplastic resin; placing the stiffeners on a tooling with a shape complementary to the shape of the part to be fabricated; simultaneously fabricating and assembling the skin with the stiffeners by lay-up and continuous consolidation of strips of long fibers impregnated with thermoplastic resin, directly on the tooling on which the stiffeners are placed; and cooling a strip that has just been deposited to a temperature below the melting temperature of the thermoplastic resin, prior to adding an additional strip heated at a temperature above the melting temperature of the thermoplastic resin to weld the strips together by diffusion. 2. Process according to claim 1, in which the stiffeners are made by continuously and automatically depositing a strip long fibers impregnated with thermoplastic resin in order to form a panel, by cutting blacks out of this panel, and then by consolidation and shaping of theses blanks. 3. Process according to claim 2, in which the blanks are consolidated before they are shaped. 4. Process according to claim 2, which the blanks are consolidated in an autoclave or in heating press. 5. Process according to claim 2, in which the blanks are shaped by thermoforming. 6. Process according to claim 5, in witch the blanks are bent before they are shaped by thermoforming. 7. Process according to claim 2, in which the blanks are consolidated and shaped simultaneously by thermoforming, in a heating press. 8. Process according to claim 1, applied to the fabrication of a hollow part, in which the stiffeners are placed in recesses formed on a mandrel forming part of the tooling, and in which the lay-up is then done and the strip is continuously consolidated on this mandrel by rotating the mandrel around its axis. 9. Process according to claim 8, applied to the fabrication of aircraft fuselage segments, in which stiffeners comprising rails, frames and local stiffeners are fabricated. 10. Process according to claim 1, in which lightning protection is then integrated into the skin.
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이 특허에 인용된 특허 (9)
Willden Kurtis S. (Kent WA) Goodno Kenneth N. (Federal Way WA), Caul and method for bonding and curing intricate composite structures.
Dull Kenneth M. (3017 Deer Island Dr. Sumner WA 98390) Schneider Terry L. (24156 Falconer Dr. Murrieta CA 92362), Edge and surface breather for high temperature composite processing.
Biornstad, Robert D.; Blankinship, Bruce C.; George, Terry J.; Ingram, William H., Composite barrel sections for aircraft fuselages and other 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.
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.
Biornstad, Robert D.; Blankinship, Bruce C.; George, Terry J.; Ingram, William H., Composite barrel sections for aircraft fuselages and other structures, and methods for systems for manufacturing such barrel sections.
Chapman, Michael R.; Watson, Robert M.; Anderson, Donald A.; Piehl, Marc J.; Sweetin, Joseph L.; Grose, Douglas L., Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections.
Chapman, Michael R.; Watson, Robert M.; Anderson, Donald A.; Piehl, Marc J.; Sweetin, Joseph L.; Grose, Douglas L., Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections.
Chapman,Michael R.; Watson,Robert M.; Anderson,Donald A.; Piehl,Marc J.; Sweetin,Joseph L.; Grose,Douglas L., Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections.
Barlag, Carsten; Steiger, Christian; Deschauer, Niels, Device and method for manufacturing a fiber-reinforced composite fuselage shell for an aircraft.
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Goodworth, Alan R.; Anthony, James A.; Forster, William V., Method of forming panels using an in-situ tape placement process and panels formed therefrom.
Frankel, Kenneth A., Methods for forming fiber reinforced composite parts having one or more selectively positioned core, structural insert, or veneer pieces integrally associated therewith.
Chapman, Michael R.; Watson, Robert M.; Anderson, Donald A.; Piehl, Marc J.; Sweetin, Joseph L.; Grose, Douglas L., Methods for manufacturing composite sections for aircraft fuselages and other structures.
Johnson,Brice A.; Spoon,Stephen S.; Darras,Randal S., Multiple head automated composite laminating machine for the fabrication of large barrel section components.
Lieven, Patrick; Delahaye, Romain, Self-stiffened skin for aircraft fuselage including stringers with a closed section and associated manufacturing method.
Grantham,Kent; Harrison,Thomas D.; Kay,Robert M.; Kuss,Michael R.; Turnmire,William W.; Venskus,Mark K.; Whitcomb,Tory R.; Christie, legal representative,Rose; Christie, deceased,Peter S., Structural panels for use in aircraft fuselages and other structures.
Martinez Cerezo, Alberto Ramon; Arevalo Rodriguez, Elena; Galiana Blanco, Jorge Juan; Jordan Carnicero, Francisco Javier, Tubular components for aeronautical fuselages and processes and jigs for its manufacturing.
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