|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B29C-065/40 B29C-070/32 B29C-051/02 B29C-053/04|
|미국특허분류(USC)||264/102; 264/160; 264/248; 264/250; 264/255; 264/257; 264/258; 264/310; 264/324; 264/339; 264/510; 264/511; 264/512; 156/189; 156/297|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 78 인용 특허 : 9|
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 re...
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 ...