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특허 상세정보

MyON담기
내보내기 페이스북 공유 카카오톡 공유

Titanium-polymer hybrid laminates

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B32B-003/12    B32B-015/08    B64C-001/00   
미국특허분류(USC) 428/593 ; 428/608 ; 428/660 ; 428/220 ; 428/332 ; 428/457 ; 428/626 ; 428/118 ; 244/119
출원번호 US-0585304 (1996-01-11)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Christensen, O'Connor, Johnson & Kindness PLLC
인용정보 피인용 횟수 : 69  인용 특허 : 59
초록
▼

The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be orie...

대표
청구항
▼

[ We claim:] [1.] A symmetrical hybrid laminate comprising:(a) a pair of layups, each of the layups comprising:(i) a heat treated beta titanium alloy foil layer comprising butt-joined foils each of thickness in the range from about 0.003 to about 0.01 inches; and(ii) a layer of polymeric composite bonded to a side of the foil layer, the polymeric layer comprising at least one ply comprising a polymeric matrix, the matrix resistant to repeated exposure to temperatures of at least about 350.degree. F., the composite having commonly aligned fibers embedded ...

이 특허에 인용된 특허 (59)

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