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특허 상세정보

Aircraft tail configuration for sonic boom reduction

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-005/02   
미국특허분류(USC) 244/001.N; 244/015; 244/130; 244/087; 244/045.R
출원번호 US-0696795 (2003-10-30)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Koestner Bertani LLP
인용정보 피인용 횟수 : 8  인용 특허 : 28
초록

A supersonic aircraft comprises a wing having upper and lower surfaces and extending from a leading edge to a trailing edge and at least two engine nacelles coupled to the lower surface of the wing on the trailing edge. The supersonic aircraft further comprises an inverted V-tail abutting to the upper side of the wing comprising a central vertical stabilizer, at least two inverted stabilizers coupled to sides of the central vertical stabilizer and coupled to the wing and supporting at least two engine nacelles, and at least two ruddervators respectively ...

대표
청구항

1. A supersonic aircraft comprising:a wing having upper and lower surfaces and extending from a leading edge to a trailing edge;at least two engine nacelles coupled to the lower surface of the wing on the trailing edge;an inverted V-tail coupled to the wing comprising a central vertical stabilizer, at least two inverted stabilizers coupled to sides of the central vertical stabilizer and coupled to the wing and supporting the at least two engine nacelles, and at least two ruddervators respectively pivotally coupled to the at least two inverted stabilizers...

이 특허에 인용된 특허 (28)

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  23. McKinney Maurice E. (Bellevue WA) Rudolph Peter K. C. (Seattle WA). Variable camber leading edge mechanism with Krueger flap. USP1984014427168.
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