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특허 상세정보

Aircraft wing leading edge high lift device with suction

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/209 ; 244/208 ; 244/130 ; 244/214
출원번호 US-0349453 (1999-07-08)
우선권정보 GB0007888 (1997-04-18)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Nixon & Vanderhye P.C.
인용정보 피인용 횟수 : 18  인용 특허 : 8
초록

An aircraft wing, wing assembly and method of reducing drag are provided. The wing asembly includes a main wing portion (10) and a leading edge high lift portion (12). The high lift portion is movable between a retracted position in which it generally merges with the main wing portion and a deployed position forwardly thereof. At least a substantial part of an upper surface (22) of the high lift portion is air permeable or perforated and in flow communication with a suction passage (30) in it. In flight, suction may be applied to the suction passage to r...

대표
청구항

[ What is claimed is:] [1.] An aircraft wing assembly including a main wing portion and a leading edge high lift, portion movable between a retracted position in which it generally merges with the main wing portion and a deployed position forwardly thereof, characterised in that at least a substantial part of an upper surface of said high lift portion is air permeable or perforated and in flow communication with a suction passage associated with said high lift portion, whereby in flight, suction may be applied to said suction passage to at least reduce t...

이 특허를 인용한 특허 피인용횟수: 18

  1. Lorkowski, Thomas. Aerodynamic body and high-lift system comprising such an aerodynamic body. USP2013048408498.
  2. Wolfgang Gleine DE; Knut Mau DE; Udo Carl DE. Aerodynamic noise reducing structure for aircraft wing slats. USP2002056394396.
  3. Shmilovich, Arvin; Yadlin, Yoram. Aircraft wing structure and associated method for addressing lift and drag. USP20181010099771.
  4. Gölling, Burkhard. Aircraft with wings and a system for minimizing the influence of unsteady flow states. USP2017059656740.
  5. Hassan, Ahmed A.; Osborne, Bradley A.; Schwimley, Scott; Billman, Garry; Billman, legal representative, Mary. Dynamic bumps for drag reduction at transonic-supersonic speeds. USP2011098016245.
  6. Schlipf, Bernhard; Hue, Xavier. High lift component for an aircraft, high lift system, method for adjusting the high lift characteristics of an aircraft and aircraft. USP2017029567064.
  7. Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.. Lift augmentation system and associated method. USP2011108033510.
  8. Hassan, Ahmed A.; JanakiRam, Ram D.; Cerchie, Dino A.. Method and device for altering the separation characteristics of flow over an aerodynamic surface via hybrid intermittent blowing and suction. USP2005056899302.
  9. Overbergh, Christian; Hautecoeur, Michel. Mobile leading edge flap for a main wing of the aerofoils of an aircraft and main wing provided with such a flap. USP2010067731128.
  10. Booher, Sr., Benjamin V.. Parasitic drag induced boundary layer reduction system and method. USP2017079701399.
  11. Gleine, Wolfgang; Mau, Knut; Carl, Udo. Pressure control system for a pressure-expandable displacement element. USP2003036536714.
  12. Reckzeh, Daniel; Goelling, Burkhard; Lengers, Matthias. Surface element for an aircraft, aircraft and method for improving high-lift generation on a surface element. USP2016039272772.
  13. Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.; Manley, David J.. System for aerodynamic flows and associated method. USP2009127635107.
  14. Boldrin, Clete M.; Hassan, Ahmed A.. Vernier active flow control effector. USP2012038128036.
  15. Boldrin,Clete M.; Hassan,Ahmed A.. Vernier active flow control effector. USP2007087255309.
  16. Dorsett, Kenneth M.. Vortex generation. USP2016119505485.
  17. McVeigh, Michael A.; Maciolek, Robert F.. Vortex generators on rotor blades to delay an onset of large oscillatory pitching moments and increase maximum lift. USP2010077748958.
  18. Reckzeh, Daniel; Goelling, Burkhard; Lengers, Matthias. Wing for an aircraft, aircraft and method for reducing aerodynamic drag and improving maximum lift. USP2016039278753.