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특허 상세정보

Lift augmentation for highly swept wing aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/06    B64C-021/04   
미국특허분류(USC) 244/199 ; 244/36 ; 244/204 ; 244/207
출원번호 US-0857397 (1992-03-25)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 23  인용 특허 : 0
초록

A pair of spaced slots, disposed on each side of an aircraft centerline and spaced well inboard of the wing leading edges, are provided in the wing upper surfaces and directed tangentially spanwise toward thin sharp leading wing edges of a highly swept, delta wing aircraft. The slots are individually connected through separate plenum chambers to separate compressed air tanks and serve, collectively, as a system for providing aircraft lift augmentation. A compressed air supply is tapped from the aircraft turbojet power plant. Suitable valves, under the co...

대표
청구항

In combination, a highly swept, delta wing aircraft and means to stimulate vortex lift on the aircraft comprising: said highly swept, delta wing aircraft having a sharp nose and a substantially thick center line profile; said thick center line profile tapering along portions of the aircraft length to highly swept, thin sharp leading edge wing surfaces; said means to stimulate vortex lift on the delta wing aircraft including a pair of spaced slots disposed on each side of, and adjacent to, said substantially thick center line of said aircraft and directed...

이 특허를 인용한 특허 피인용횟수: 23

  1. Rist, Ulrich; Knoll, Andreas. Aerodynamic body, regulating flap or main wing or fin of an aircraft as well as a structural component with such an aerodynamic body. USP2014068757556.
  2. King ; Sr. Lloyd Herbert. Air craft wing. USP2000086109565.
  3. Clark,Walter D.. Aircraft with topside only spoilers. USP2006097108230.
  4. Glezer, Ari; DeSalvo, Michael Edward. Airfoil performance modification using synthetic jet actuators. USP2010117823839.
  5. Zha, Gecheng; Aspe, Sebastian; Dussling, Joseph John; Heinz, Nicholas Ramsay; Martinez, Daniel J.. Co-flow jet aircraft. USP2012098262031.
  6. Miller, Daniel N.; Young, David D.. Conformal aero-adaptive nozzle/aftbody. USP2010037686256.
  7. Zha, Gecheng; Dano, Bertrand P. E.. Discrete co-flow jet (DCFJ) airfoil. USP2013078485476.
  8. Guigné, Jacques Y.; Davidson, Ron. Drag reduction device for transport vehicles having randomized irregular shaped edge vortex generating channels. USP2014068757701.
  9. Long, Donald James. Fluid dynamic body having escapelet openings for reducing induced and interference drag, and energizing stagnant flow. USP2014028651813.
  10. Zha, Gecheng. Fluid systems that include a co-flow jet. USP20181010106246.
  11. Zha, Gecheng. Fluid systems that include a co-flow jet. USP20190410252789.
  12. Westra, Bryan Wayne; Sato, Roxanne Marie; Shultz, Douglas Ellwood; Kerswell, James Franklin; Petersen, Perry Bruce; Collins, Scott Walter. Flying wing aircraft with modular missionized elements. USP2012108292220.
  13. Chase, James D.; Henderson, Michael; Peter, Sturdza. Highly efficient supersonic laminar flow wing structure. USP2016019233755.
  14. Chase, James D.; Henderson, Michael; Peter, Sturdza. Highly efficient transonic laminar flow wing. USP2015038991768.
  15. Stephen M. Ruffin. Leading edge channel for enhancement of lift/drag ratio and reduction of sonic boom. USP2002106464171.
  16. Dixon Charles J.. Method and apparatus for generating a stable leading-edge lifting-vortex controller. USP2001116318677.
  17. Keefe Laurence R.. Method and apparatus for reducing the drag of flows over surfaces. USP1998095803409.
  18. Clark, Walter D.. Method and system for flying an aircraft. USP2004096793171.
  19. Wakayama,Sean R.. Reconfiguration control system for an aircraft wing. USP2008117455264.
  20. Lang, James D.. Reducing runway requirement for aircraft. USP2011087997528.
  21. Arata Allen A.. Single surface independent aircraft control. USP2001056227498.
  22. Arata Allen A.. Single surface multi axis aircraft control. USP2000056068219.
  23. Gutmark Ephraim J. ; Guillot Stephen A.. Vortical lift control over a highly swept wing. USP2000106138955.