IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0642572
(1984-08-20)
|
발명자
/ 주소 |
- Braun Rudolf (Winnipeg CAX) Jensen Richard (Winnipeg CAX)
|
출원인 / 주소 |
- The Boeing Company (Seattle WA 02)
|
인용정보 |
피인용 횟수 :
17 인용 특허 :
4 |
초록
▼
This invention relates to an improved composite material leading edge/spar member for an aircraft control surface, and the like. The present invention provides a one-piece composite leading edge/spar member that is of a lighter and stronger construction offering dimensional stability, and an efficie
This invention relates to an improved composite material leading edge/spar member for an aircraft control surface, and the like. The present invention provides a one-piece composite leading edge/spar member that is of a lighter and stronger construction offering dimensional stability, and an efficient method for manufacturing the same is also provided. A one-piece leading edge/spar member (12) includes a forward leading edge portion (22), and an aft spar portion (23). The forward leading edge and the aft spar portions are connected together as a continuous one-piece tubular member of composite material. The forward leading edge portion (22) may be rounded, and the aft spar portion (23) may include an aft web portion (24) and first and second rebate portions (26, 28). The rebate portions (26, 28) connect the web portion (24) to the rounded forward leading edge portion (22), and provide surfaces for the attachment of skin surface members (16, 18) thereto.
대표청구항
▼
A method of fabricating an aircraft control surface, or the like, the method comprising the following steps: (a) Providing a mandrel shaped to have a rounded leading edge forming portion and a spar forming portion, said spar forming portion including first and second rebate forming portions each of
A method of fabricating an aircraft control surface, or the like, the method comprising the following steps: (a) Providing a mandrel shaped to have a rounded leading edge forming portion and a spar forming portion, said spar forming portion including first and second rebate forming portions each of which is connected to said rounded leading edge portion, said spar forming portion further including a web forming portion which interconnects said first and second rebate forming portions; (b) applying a composite material to said mandrel, with said material perimetrically surrounding and covering said rounded leading edge portion and said spar forming portion; (c) positioning said covered mandrel in abutting relationship adjacent a supporting surface, so that the covered web forming portion of said spar forming portion abuts said surface, and positioning a separate caulplate against each of the covered rebate forming portions of said spar forming portion, and positioning still another caulplate against the covered rounded leading edge forming portion of said mandrel, wherein said caulplates and said supporting surface cooperate with each other to substantially surround said covered mandrel; (d) curing said composite material to set in the shape of said mandrel, to form a one-piece leading edge/spar member, including applying forming pressure to said caulplates and to said supporting surface in a manner so as to force said caul plates and said supporting surface against said composite material, and including heating and thermally expanding said mandrel at the same time said forming pressure is applied, such expansion forcing said composite material outwardly and against said caulplates and said supporting surface, wherein said forming pressure applied to said caulplates and to said supporting surface together with said thermal expansion shape and mold said material into the same shape as said mandrel; (e) after forming said one-piece leading edge/spar member, attaching a leading side of a first skin member to one of the formed rebate portions of said leading edge/spar member, in a manner so that the formed rounded leading edge portion of said leading edge/spar member and said first skin surface member form a substantially continuous aerodynamic surface; (f) attaching a generally wedge-shaped trailing edge member to a trailing side of said first skin surface member; (g) attaching a generally wedge-shaped honeycomb core member to said leading edge/spar member, and to said first skin surface member, and to said trailing edge member, wherein said honeycomb member includes a forward end surface connected to the web portion of said leading edge/spar member, and an aft end surface connected to said trailing edge member, and upper and lower honeycomb side surfaces, wherein one of said side honeycomb surfaces is connected to said first skin surface member; (h) attaching a leading side of a second skin surface member to the other of said rebate portions of said leading edge/spar member, in a manner so that said rounded leading edge portion of said leading edge/spar member and said second surface member form a substantially continuous aerodynamic surface, and attaching said second skin surface member to the other of said honeycomb side surfaces, and to said trailing edge member, and wherein said leading edge/spar member, said honeycomb member, said trailing edge member, and said first and second skin surface members together form said control surface; and (i) curing said control surface.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.