[특허]Low sonic boom inlet for supersonic aircraft

Techland Research, Inc.

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

특허 상세정보

MyON담기

내보내기

Low sonic boom inlet for supersonic aircraft

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64B-001/24 B64B-001/00
미국특허분류(USC)	244/053.B; 137/015.1
출원번호	US-0966551 (2001-09-26)
발명자 / 주소	Sanders,Bobby W. Weir,Lois J.
출원인 / 주소	Techland Research, Inc.
대리인 / 주소	Calfee, Halter &
인용정보	피인용 횟수 : 40 인용 특허 : 6

초록
▼

All-internal compression inlets for supersonic aircraft, with variable geometry systems and shock stability bleed systems provide high performance, large operability margins, i.e. terminal shock stability that reduces the probability of inlet unstart, and contribute little or nothing to the overall sonic boom signature of the aircraft. These inlets have very high internal area contraction or compression and very low external surface angles. All shocks from the internal inlet surfaces are captured and reflected inside the inlet duct, and all of the external nacelle surfaces are substantially aligned with the external airflow. The inlet shock stability system consists of bleed regions that duct bleed airflows to variable area exits with passive or active exit area controls. This reduces the risk of inlet unstarts by removing airflow through a large open throat bleed region to compensate for reductions in diffuser (engine) corrected airflow demand. Because the stability bleed is not removed until the inlet terminal shock moves upstream over the bleed region, the necessary normal shock operability margin is provided without compromising inlet performance (total pressure recovery, and distortion).

대표
청구항
▼

We claim: 1. A supersonic inlet for use with an aircraft, said supersonic inlet comprising: an internal duct having an opening for receiving airflow and a throat section, said inlet further comprising one or more external surfaces wherein said one or more entire external surfaces are aligned with the flow of the aircraft, said opening of said internal duct further comprised of a first and second leading edge, wherein said leading edges are staggered in location; and said throat section of the inlet further incorporating a shock stability bleed system, wherein a portion of said airflow is removed from said internal duct so that a shock wave is maintained within said throat section. 2. A supersonic inlet for use with an aircraft, said supersonic inlet comprising: an internal duct having an opening for receiving airflow and a throat section, said inlet having one or more external surfaces aligned with the airflow of said aircraft, a centerbody positioned within said duct, and having a leading edge, the external surfaces being aligned with the airflow of the aircraft from the leading edge to an associated engine; said opening of said internal duct further comprised of a leading edge, wherein said leading edge of said duct is staggered in location with respect to the leading edge of the centerbody; and said throat section of the inlet further includes a shock stability bleed system, wherein a portion of said airflow is removed from said internal duct so that a shock wave i maintained within said throat section. 3. The inlet of claim 1 wherein all of the external surfaces are aligned with the airflow of the aircraft. 4. The inlet of claim 1 wherein one or more of the external surfaces are aligned with the airflow of the aircraft at all operating conditions. 5. The inlet of claim 1 wherein said internal duct comprises one or more movable compression surfaces. 6. The inlet of claim 1 wherein said one or more external compression surfaces are fixed in location. 7. The inlet of claim 2 wherein all of the external surfaces are aligned with the airflow of the aircraft. 8. The inlet of claim 2 wherein one or more of the external surfaces are aligned with the airflow of the aircraft at all operating conditions. 9. The inlet of claim 2 wherein said internal duct comprises one or more movable compression surfaces. 10. The inlet of claim 2 wherein said one or more external compression surfaces are fixed in location. 11. A low boom supersonic inlet for use with an aircraft engine, the supersonic inlet comprising: one or more internal surfaces forming an internal duct to provide airflow to the aircraft engine and having an opening for receiving airflow; and one or more external surfaces that are entirely aligned with the flow of air to the inlet whereby the inlet external shock waves that contribute to the sonic boom signature of the aircraft have been substantially reduced. 12. The low sonic boom supersonic inlet of claim 11 wherein said internal surfaces provide supersonic compression and are movable into two or more positions. 13. The low sonic boom supersonic inlet of claim 11 wherein said internal surfaces extend from the leading edge to the engine entrance, said internal surfaces comprising one or more compression surfaces for providing supersonic compression of the air to the inlet throat and subsonic diffusion of the air to the engine entrance. 14. The low sonic boom supersonic inlet of claim 11 wherein said internal duct further comprises a throat section having a shock stability bleed system comprised of one or more bleed passageways wherein a portion of said airflow is removed from said internal duct through said one or more bleed passageways so that an airflow shock wave is maintained within said throat region. 15. The low sonic boom supersonic inlet of claim 11 wherein all of the compression surfaces are located within said internal duct. 16. The low sonic boom supersonic inlet of claim 15 wherein excess air not required by the engine is ducted out of the inlet through an overboard bypass system. 17. The low sonic boom supersonic inlet of claim 11 wherein said internal duct has a rectangular cross-sectional shape. 18. The low sonic boom supersonic inlet of claim 11 wherein said internal duct has a elliptical cross-sectional shape. 19. The low sonic boom supersonic inlet of claim 1 wherein said internal duct has a rectangular cross-sectional shape. 20. The low sonic boom supersonic inlet of claim 1 wherein said internal duct has a elliptical cross-sectional shape. 21. The low sonic boom supersonic inlet of claim 2 wherein said internal duct has a rectangular cross-sectional shape. 22. The low sonic boom supersonic inlet of claim 2 wherein said internal duct has a elliptical cross-sectional shape. 23. The low sonic boom supersonic inlet of claim 1 wherein said shock stability bleed system further comprises bleed passages having a variable area exit. 24. The low sonic boom supersonic inlet of claim 1 wherein said throat section of said inlet further comprises one or more movable internal sidewalls in the throat section for varying the throat area. 25. The low sonic boom supersonic inlet of claim 1 wherein the interior surfaces of the internal duct have continuous surfaces from the opening to the exit of the inlet.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 40

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

Low sonic boom inlet for supersonic aircraft

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 40

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Low sonic boom inlet for supersonic aircraft

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 40

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼