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특허 상세정보

Swept gradient boundary layer diverter

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02    B64C-021/10    B64C-023/06    B64C-023/04    B64D-047/08   
출원번호 US-0750718 (2015-06-25)
등록번호 US-9758253 (2017-09-12)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Miller, John A.
인용정보 피인용 횟수 : 0  인용 특허 : 24
초록

A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to an...

대표
청구항

1. An air boundary layer diverter for an aircraft, said aircraft including a fuselage and at least one engine air inlet for an engine of the aircraft, said engine air inlet including a shaped cowl at a leading edge of the engine air inlet defining an opening through which air flows to the engine, said diverter comprising: a ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft; anda trough portion formed in t...

이 특허에 인용된 특허 (24)

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  2. Parikh, Pradip G.; Willie, Robert H.. Air inlet and method for a highspeed mobile platform. USP2011017861968.
  3. Da Silva, Carlos Roberto Ilário; Roncatto, André Luis; Belém, Antônio Nunes; Da Cunha, Marcelo Faria. Aircraft air inlet diverter assemblies with improved aerodynamic characteristics. USP2015069051057.
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  5. Lucchesini, Massimo; Merlo, Emanuele. Aircraft with improved aerodynamic performance. USP2016039284046.
  6. Chanez, Philippe Gerard; Lecordix, Jean-Loic Herve; Thomas, Stephane Jacques Francois. Airplane having engines partially encased in the fuselage. USP2014048684302.
  7. Leland, Bradley C.; Klinge, John D.; Lundy, Brian F.. Apparatus and method for processing airflow with flowfield molded hypersonic inlet. USP2012108297058.
  8. Koncsek Joseph L. (Seattle WA) McMahon Steven L. (Lake Stevens WA). Ducted boundary layer diverter. USP1996025490644.
  9. Smith, Thomas R.; Espinosa, Angel M.; Farrell, Daniel J.; Robertson, Andrew; Leylegian, John C.; Tyll, Jason S.; Girlea, Florin; Alifano, Joseph A.; Chue, Randy S. M.. Hypersonic inlet systems and methods. USP2012108292217.
  10. Silkey, Joseph S.; Wilson, Christopher D.; Dyer, Richard S.. Inlet distortion and recovery control system. USP2009127637455.
  11. Nelson, Chester P.. Integrated and/or modular high-speed aircraft. USP2003066575406.
  12. Smith, Thomas R.; Bowcutt, Kevin G.. Integrated hypersonic inlet design. USP2012098256706.
  13. Elvin, John D.. Integrated inward turning inlets and nozzles for hypersonic air vehicles. USP2011017866599.
  14. Leland, Bradley C.; Klinge, John D.; Lundy, Brian F.. Method for designing flowfield molded hypersonic inlet for integrated turbojet and ram-scramjet applications. USP2009087568347.
  15. McMaster Daniel ; Breidenthal ; Jr. Robert Edward. Passive flow control aero-optical turret assembly. USP1998075775643.
  16. Seidel, Gerhard E.. Separate boundary layer engine inlet. USP2003036527224.
  17. Chase, James D.; Garzon, German Andres. Supersonic aircraft jet engine installation. USP2011067967241.
  18. Sanders, Bobby W.; Koncsek, Joseph L.; Hedges, Linda S.. Supersonic external-compression diffuser and method for designing same. USP2004096793175.
  19. Hamstra Jeffrey William ; Sylvester Thomas Gerard. System and method for diverting boundary layer air. USP1998075779189.
  20. Lundy,Brian F.; Klinge,John D.; Leland,Bradley C.. System, method, and apparatus for designing streamline traced, mixed compression inlets for aircraft engines. USP2007047207520.
  21. Leland, Bradley C.; Lundy, Brian F.; Klinge, John D.. System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines. USP2010047690595.
  22. Hamstra Jeffrey William ; McCallum Brent Neal ; Sylvester Thomas Gerard ; Denner Brett Willian ; Moorehouse Jeffrey Allen. Transition shoulder system and method for diverting boundary layer air. USP1998055749542.
  23. Huynh, Thuy. Variable-geometry rotating spiral cone engine inlet compression system and method. USP2014048690097.
  24. Da Silva, Luis Fernando Figueira; Ferreira, Sandro Barros; Perez, Cesar Celis; Oliveira, Guilherme Lara; De Jesus, Antonio Batista. Vortex generators to improve performance of flush air inlets. USP2013108544799.