Method and apparatus for manufacturing composite structures
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IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B29C-070/32
B29C-070/36
B29C-043/56
출원번호
US-0790559
(1997-01-29)
발명자
/ 주소
Lunde, Gerald A.
출원인 / 주소
Raytheon Aircraft Company
대리인 / 주소
Schubert, William C.Lenzen, Jr., Glenn H.
인용정보
피인용 횟수 :
121인용 특허 :
7
초록▼
Composite structures having a single continuous skin may be formed using automated fiber placement methods. These composite structures include frameless aircraft fuselage components offering an increased interior cabin width over conventional fuselage components. The composite structures may be cons
Composite structures having a single continuous skin may be formed using automated fiber placement methods. These composite structures include frameless aircraft fuselage components offering an increased interior cabin width over conventional fuselage components. The composite structures may be constructed of multiple layers of fibers and other materials placed on a fiber placement tool that includes a mandrel body surrounded by a bladder or an integral bladder/caul sheet having expansion spaces created within the caul sheet section. Uncured composite structures may be created by placing fibers around the fiber placement tool in a plurality of discontinuous segments that are capable of moving or sliding in relation to each other so that the uncured composite structure is expandable from within. Fluid openings may be provided in the outer surface of the mandrel body for the application of vacuum and/or fluid pressure to secure the bladder to the mandrel body and to assist in the removal of the bladder from the mandrel body, respectively. Uncured composite structures may be sealed between the bladder and is clam shell molds. The uncured structures may be expanded against the inner surface of the molds by creating a vacuum between the bladder and molds.
대표청구항▼
Composite structures having a single continuous skin may be formed using automated fiber placement methods. These composite structures include frameless aircraft fuselage components offering an increased interior cabin width over conventional fuselage components. The composite structures may be cons
Composite structures having a single continuous skin may be formed using automated fiber placement methods. These composite structures include frameless aircraft fuselage components offering an increased interior cabin width over conventional fuselage components. The composite structures may be constructed of multiple layers of fibers and other materials placed on a fiber placement tool that includes a mandrel body surrounded by a bladder or an integral bladder/caul sheet having expansion spaces created within the caul sheet section. Uncured composite structures may be created by placing fibers around the fiber placement tool in a plurality of discontinuous segments that are capable of moving or sliding in relation to each other so that the uncured composite structure is expandable from within. Fluid openings may be provided in the outer surface of the mandrel body for the application of vacuum and/or fluid pressure to secure the bladder to the mandrel body and to assist in the removal of the bladder from the mandrel body, respectively. Uncured composite structures may be sealed between the bladder and is clam shell molds. The uncured structures may be expanded against the inner surface of the molds by creating a vacuum between the bladder and molds. rs Squibb Company), Warsaw (1977). Atkinson, J.R. et al., "Silane cross-linked polyethylene for prosthetic applications. Part I. Certain physical and mechanical properties related to the nature of the material", Biomaterials, 4:267 (1983). Atkinson, J.R. et al., "Silane cross-liked polyethylene for prosthetic applications. Part II. Creep and wear behavior and a preliminary moulding test", Biomaterials, 5:326 (1984). 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