$\require{mediawiki-texvc}$
  • 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"
쳇봇 이모티콘
안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

Variable geometry inlet design for scram jet engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-007/08   
미국특허분류(USC) 060/768; 060/767
출원번호 US-0264172 (2002-10-02)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Bachman &
인용정보 피인용 횟수 : 4  인용 특허 : 11
초록

The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading e...

대표
청구항

1. A variable geometry inlet for a scram jet engine having at least one combustor module, said inlet comprising:each said combustor module having two sidewalls; each said sidewall having a central portion with a thickness and a tapered profile forward of said central portion which terminates in a sharp leading edge; each said module having a lower wall and a movable cowl flap positioned forward of said lower wall; and said movable cowl flap having a leading edge. 2. A variable geometry inlet according to claim 1, further comprising:said leading edges of ...

이 특허에 인용된 특허 (11)

  1. Chevalier Alain,FRX ; Bouchez Marc,FRX. Fuel injection device for ramjets for aircraft. USP1999085941064.
  2. Chevalier Alain,FRX ; Bouchez Marc,FRX. Fuel-injecting apparatus for ramjet engine cooled by transpiration. USP2000126164061.
  3. Baker Clifford B. (Rockville MD) Keirsey James L. (Rockville MD). Hypersonic modular inlet. USP1980034194519.
  4. Bichler Bartholomus (Raubling DEX) Jost Michael (Munich DEX). Inlet system for supersonic or hypersonic aircraft. USP1992055116251.
  5. Kutschenreuter ; Jr. Paul H. (Loveland OH) Blanton John C. (West Chester OH). Method of operating a scramjet including integrated inlet and combustor. USP1993105255513.
  6. Enderle Heinrich (Grbenzell DEX). Propelling nozzle for a hypersonic jet plane. USP1992035094070.
  7. Bouchez, Marc; Falempin, Fran.cedilla.ois; Levine, Vadim. Ramjet for a supersonic and hypersonic aircraft. USP2004016672068.
  8. Sillence, Mark A.; Guinan, Daniel P.; Nemecek, Dennis J.; Salvador, Costante; Webster, Henry K.; Fortin, Thomas B.; Rinella, Sergio; Nigam, Revi K.. Scram jet engine design. USP2004046715293.
  9. Billig Frederick S. (Rockville MD) VanWie David M. (Brookeville MD). Translating cowl inlet with retractable propellant injection struts. USP1993065214914.
  10. Jabs Alfred (Groebenzell DEX). Turboramjet engine. USP1992035094071.
  11. Falempin Francois (Saint Arnoult en Yvelines FRX) Fourt Olivier (Jouy en Josas FRX) Pastre Jean-Louis (Sainte Genevieve des Bois FRX). Two-dimensional supersonic and hypersonic air intake, with three movable ramps, for the combustion air of an aircraft en. USP1996125586735.