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특허 상세정보

Surface element for an aircraft, aircraft and method for improving high-lift generation on a surface element

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/04    B64C-021/02    B64C-009/24    B64C-021/06   
출원번호 US-0850414 (2013-03-26)
등록번호 US-9272772 (2016-03-01)
우선권정보 EP-12162149 (2012-03-29)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Lerner, David, Littenberg, Krumholz & Mentlik, LLP
인용정보 피인용 횟수 : 2  인용 특허 : 42

A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an ...


1. An aircraft wing comprising: a leading edge,a high lift device arrangement positioned along the leading edge,at least one add-on body comprising an engine positioned in a leading edge region, the engine having an engine mounting center line,wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body,wherein the wing comprises an arrangement of openings in a region covering the add-on body, said openings connected to an air conveying device for conveying air through the...

이 특허에 인용된 특허 (42)

  1. Hassan Ahmed A. ; Straub Friedrich K. ; Domzalski David B. ; Kennedy Dennis K.. Active blowing system for rotorcraft vortex interaction noise reduction. USP1998095813625.
  2. Taylor Robert M. (Vienna VA). Aerodynamic surface tip vortex attenuation system. USP1992105158251.
  3. Brown, James. Aerofoil slot blowing. USP2013118573542.
  4. King ; Sr. Lloyd Herbert. Air craft wing. USP2000086109565.
  5. Collett Edward,GBX. Aircraft wing leading edge high lift device with suction. USP2000106135395.
  6. Johnstone Edmund H. (82 Salzburg Blvd. Apt. G Columbus IN 47201). Aircraft wing vortex deflector. USP1976083974986.
  7. Swanson ; Everts W. ; Wehrman ; Marvin D.. Boundary layer control system for aircraft. USP1978074099691.
  8. Kelber Charles C. (2081 Snowden Ave. Long Beach CA 90815). Combination lift thrust device. USP1987054666104.
  9. Jonker, Adrianus Stefanus; Bosman, Johannes Jacobus. Controlling the boundary layer of an airfoil. USP2012088251319.
  10. Syassen, Freerk. Device for reducing the aerodynamic drag of a leading surface of an aircraft. USP2014108864082.
  11. Anxionnaz Rene (8 ; RUE Nicolas Chuquet 75-Paris FR). Device for regulating and recovering the boundary layer over the surface of a body such as an aircraft in flight. USP1976043951360.
  12. Carson,Dale C.. Drag reduction system and method. USP2006027004094.
  13. Kloker, Markus; Messing, Ralf. Flow surface for a three-dimensional boundary-layer flow, especially on a swept wing, a swept tail plane or a rotor. USP2010067735782.
  14. Long, Donald James. Fluid dynamic body having escapelet openings for reducing induced and interference drag, and energizing stagnant flow. USP2014028651813.
  15. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2014098844264.
  16. Tamura Raymond M. (218 Lagoon Dr. Honolulu HI 96819). Helicopter lifting and propelling apparatus. USP1979104169567.
  17. Rudolph Peter K. C. (Seattle WA). High taper wing tip extension. USP1991085039032.
  18. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2010087766280.
  19. Williams, Stewart W; Turner, Brian J. Laminar flow control system and suction panel for use therewith. USP2004066752358.
  20. Crouch, Jeffrey D.; Ng, Lian L.; Sutanto, Mary I.. Laminar flow surfaces with selected roughness distributions, and associated methods. USP2010127850126.
  21. Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.. Lift augmentation system and associated method. USP2011108033510.
  22. Raghu, Surya. Method and apparatus for aerodynamic flow control using compact high-frequency fluidic actuator arrays. USP2013028382043.
  23. Keefe Laurence R.. Method and apparatus for reducing the drag of flows over surfaces. USP1998095803409.
  24. Whitmore, Stephen A.; Saltzman, Edwin J.; Moes, Timothy R.; Iliff, Kenneth W.. Method for reducing the drag of blunt-based vehicles by adaptively increasing forebody roughness. USP2005056892989.
  25. Shatz Solomon (P.O. Box 523 Cupertino CA 94015). Movable sheet for laminar flow and deicing. USP1997015590854.
  26. Al-Garni, Ahmed Z.; Al-Qutub, Amro M.. Movable surface plane. USP2003096622973.
  27. Hassan Ahmed A. ; Tadghighi Hormoz ; Janakiram Ram D.. Oscillating air jets for reducing HSI noise. USP2001056234751.
  28. Parikh, Pradip G.. Passive removal of suction air for laminar flow control, and associated systems and methods. USP2011017866609.
  29. Bertolotti,Fabio P.. Perforated skin structure for laminar-flow systems. USP2006127152829.
  30. Horstman Raymond H. (Auburn WA). Perforated wing panel with variable porosity. USP1993115263667.
  31. Tamura Raymond M. (218 Lagoon Dr. Honolulu HI 96819). Pollution reducing aircraft propulsion. USP1980074214722.
  32. Meister Juergen,DEX ; Pfennig Juergen,DEX ; Held Werner,DEX. Rudder assembly with a controlled boundary layer control for an aircraft. USP1999055899416.
  33. Hwang Danny P.. Skin friction reduction by micro-blowing technique. USP1998095803410.
  34. Pfennig Juergen,DEX ; Meister Juergen,DEX. Suction device for boundary layer control in an aircraft. USP2001046216982.
  35. Breit Hubert,DEX. Suction generator system in an aircraft for maintaining a laminar boundary flow. USP1999035884873.
  36. Pal, Anadish Kumar. Surface flow diverting and static charging ducted pores on wing or blade tip to reduce wake and BVI noise. USP2009127637462.
  37. Owens Phillip R. (1417 Kirby St. ; NE. Albuquerque NM 87112). V/STOL aircraft and method. USP1997115687934.
  38. Griswold ; II Roger W. (Ben Franklin Rd. Old Lyme CT 06371). Vortex alleviating wing tip. USP1984104477042.
  39. Yuan Shao Wen (2021 Highboro Way Falls Church VA 22043). Vortex control. USP1976023936013.
  40. Lewis Delbert S. (Bellevue WA). Wing leading edge high lift device. USP1981084285482.
  41. Boppe, Charles W.; Harvie, Stuart G.. Wing tip flow control. USP1983054382569.
  42. Ransick Thomas F. (Rockford IL). Wingtip turbine. USP1992095150859.