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특허 상세정보

Inlet system for supersonic or hypersonic aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02   
미국특허분류(USC) 244/53B ; 137/151 ; 60/2701
출원번호 US-0671121 (1991-03-18)
우선권정보 DE-4008956 (1990-03-20)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 15  인용 특허 : 0

An inlet system, which can be used for all supersonic or hypersonic engine inlets, comprises two or several separate parallel ducts which must be switched over in specific phases of flight. This is accomplished with a duct shaped parallel inlet element pivotably assigned to the inlet ramp of the inlet, which as a channel-connecting re-direction member alternately can close off the turbojet inlet duct as well as also the ramjet inlet. Preferably, the construction comprises a plurality of pivotably connected box-like elements interconnected in a movable ma...


An inlet system for supersonic and hypersonic aircraft for supplying air to substantially parallel turbojet and ramjet engine inlets, comprising a pivotable inlet ramp having a box shaped configuration for changing the inlet cross-section, said inlet ramp comprising a plurality of hollow box-like elements bounded by walls on all sides, means for pivotably supporting said box-like elements with respect to each other, a pivotable inlet plate upstream of the box-like elements, and a pivotably arranged re-direction member connected with the inlet ramp downst...

이 특허를 인용한 특허 피인용횟수: 15

  1. Laurant, Franck; Bellet, Francois; Joret, Jean-Philippe. Composite panel having a built-in duct. USP2016089410485.
  2. Cuva,William J.; Paulus,Donald E.. Cooling scheme for scramjet variable geometry hardware. USP2006107117680.
  3. Boehnlein, John; Bendot, Joseph; Schoelen, Francis. Ejector based engines. USP2004096786040.
  4. Jarmon, David C.; Sillence, Mark A.; Attridge, Paul; Yamanis, Jean. Flowpath heat exchanger for thermal management and power generation within a hypersonic vehicle. USP2012038127555.
  5. Smith David R. (West Haven CT) Amelio Armand F. (New Milford CT). Low observable engine air inlet system. USP1997125697394.
  6. Leland, Bradley C.; Klinge, John D.; Lundy, Brian F.. Method for designing flowfield molded hypersonic inlet for integrated turbojet and ram-scramjet applications. USP2009087568347.
  7. Dyer, Richard S.; Kaemming, Thomas A.; Horne, III, Samuel E.. Multi-path inlet for aircraft engine. USP2012078210474.
  8. Sheoran, Yogendra Y.; Bouldin, Bruce D.. Plenum entry bulk swirl generator. USP2003026520738.
  9. Clapp Mitchell B. ; Zubrin Robert M.. Reusable rocket-propelled high altitude airplane and method and apparatus for mid-air oxidizer transfer to said airplane. USP2000096119985.
  10. Arata, Allen A.. SCRAMjet arrangement for hypersonic aircraft. USP2010117828243.
  11. 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.
  12. Sanders, Bobby W.; Koncsek, Joseph L.; Hedges, Linda S.. Supersonic external-compression diffuser and method for designing same. USP2004096793175.
  13. Huynh, Thuy; Werner, Eric. Variable geometry flush boundary diverter. USP2018019862482.
  14. Lamb, Jr., Donald William. Variable geometry helicopter engine inlet. USP2017059656760.
  15. Guinan, Daniel P.; Drake, Alan; Andreadis, Dean; Beckel, Stephen A.. Variable geometry inlet design for scram jet engine. USP2005046883330.