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특허 상세정보

Wing leading edge architecture suitable for laminar flow

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/02    B64C-003/14    B64C-009/24    B64C-009/34    B64D-015/04   
출원번호 US-0271477 (2014-05-07)
등록번호 US-9896190 (2018-02-20)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Ostranger Chong Flaherty & Broitman P.C.
인용정보 피인용 횟수 : 0  인용 특허 : 24
초록

A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portions adjacent to side edge portions of adjacent leading edge skin panels and along an aft edge portion overlapping a wing skin. In addition, the embodiments disclosed herein integrate a low-drag bleed-air anti-icing (i.e., vent) system and a Krueger flap assembly...

대표
청구항

1. A wing assembly comprising: a spar;an upper wing skin joined to said spar, said upper wing skin comprising a forward extension that extends forward of said spar and includes a mating surface offset from a surface of said upper wing skin;a first rib fixedly coupled to and projecting forward from said spar;a fixed leading edge skin panel fixedly coupled to said first rib, wherein said fixed leading edge skin panel comprises an upper portion and a lower portion;an upper chord connected to said upper portion of said fixed leading edge skin panel;a lower c...

이 특허에 인용된 특허 (24)

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