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특허 상세정보

Apparatus for influencing a wing root airflow in an aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/06   
미국특허분류(USC) 244/199 ; 244/214 ; 244/130
출원번호 US-0078292 (1998-05-13)
우선권정보 DE9719922 (1997-05-13)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Fasse
인용정보 피인용 횟수 : 18  인용 특허 : 10
초록

An apparatus advantageously influences the wing root airflow along the wing root of an aircraft having a high lift system including leading edge slats provided on the main wings. The apparatus includes a respective vortex generator arranged on the inboard end of each leading edge slat in the area of the wing root, and further includes a respective transition fairing arranged on a separation edge that is let into the leading edge of the wing root and that borders along the inboard edge of the respective slat. The vortex generator is a rigid member fixed t...

대표
청구항

[ What is claimed is:] [1.] In an aircraft having a fuselage, a wing connected to said fuselage at a root area of said wing, and a leading edge slat movably arranged at a leading edge of said wing so as to be extendable to an extended position and retractable to a retracted position relative to said wing, an improved apparatus for influencing a wing root airflow over said wing at said root area, wherein said wing has a separation edge let into said leading edge adjacent said root area, an inboard edge of said slat borders along said separation edge when ...

이 특허를 인용한 특허 피인용횟수: 18

  1. Wolfgang Gleine DE; Knut Mau DE; Udo Carl DE. Aerodynamic noise reducing structure for aircraft wing slats. USP2002056394396.
  2. Okabe, Yoshinori; Ishihara, Kenya; Sugawara, Zenta. Aircraft. USP20180710017240.
  3. Fol, Thierry; Jimenez, Philippe; Namer, Arnaud. Aircraft comprising a central fairing that adjusts the pressure on the wing structures by means of local geometric deformations. USP2012058177170.
  4. Lucchesini, Massimo; Iaia, Pierclaudio. Aircraft configuration with improved aerodynamic performance. USP2009047520470.
  5. Morgenstern, John M.; Arslan, Alan. Aircraft lift device for low sonic boom. USP2005086935592.
  6. Dodd, Daniel; Cathelain, Francois. Aircraft wing. USP2013018353483.
  7. Clark, Walter Dennis. Aircraft with forward opening inlay spoilers for yaw control. USP2005056892982.
  8. Ferrari, Marcello do Areal Souto. Devices and methods to improve wing aerodynamics at low airspeeds. USP2012028118265.
  9. Whitehouse, Ian Roy; Kay, Edmund; Dodd, Daniel. High-lift device for an aircraft. USP2012038128038.
  10. Chase, James D.; Henderson, Michael; Peter, Sturdza. Highly efficient supersonic laminar flow wing structure. USP2016019233755.
  11. Chase, James D.; Henderson, Michael; Peter, Sturdza. Highly efficient transonic laminar flow wing. USP2015038991768.
  12. Dunavan, Marcus A.. Leading edge snag for exposed propeller engine installation. USP2014068740139.
  13. Huenecke, Klaus. Method and apparatus for reducing trailing vortices in the wake of an aircraft. USP2003026513761.
  14. Konings, Christopher A.. Nacelle chine installation for drag reduction. USP2005116964397.
  15. Ingo Borchers DE; Roger Drobietz DE; Michael Gruenewald DE; Knut Mau DE; Johann Reichenberger DE. Noise reducing vortex generators on aircraft wing control surfaces. USP2002126491260.
  16. Sclafani, Anthony J.; Konings, Christopher A.. Retractable nacelle chine. USP2012018087617.
  17. Kafyeke, Fassi; Langlois, Marc; Kho, Cedric. Slat configuration for fixed-wing aircraft. USP2014078789798.
  18. Robertson, Paul E.. Wing root leading edge extension. USP201604D754053.