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특허 상세정보

Apparatus and method for the control of trailing wake flows

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/00   
미국특허분류(USC) 244/199.3; 244/207
출원번호 UP-0332835 (2006-01-13)
등록번호 US-7597289 (2009-10-20)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Perkins Coie LLP
인용정보 피인용 횟수 : 2  인용 특허 : 35

A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.


We claim: 1. An airfoil vortex dissipating system comprising: an airfoil having a leading edge, a trailing edge, and an outer end portion; and at least one nozzle positioned at, or proximate to, the outer end portion of the airfoil, wherein a characteristic of the at least one nozzle cyclically changes during operation to discharge a jet air stream in a plurality of different discharge directions, wherein the characteristic changes at a cyclic frequency sufficient to substantially dissipate a vortex generated by the airfoil. 2. The system of claim 1 ...

이 특허에 인용된 특허 (35)

  1. Hassan Ahmed A. ; Straub Friedrich K. ; Domzalski David B. ; Kennedy Dennis K.. Active blowing system for rotorcraft vortex interaction noise reduction. USP1998095813625.
  2. Crouch Jeffrey D. ; Spalart Philippe R.. Active system for early destruction of trailing vortices. USP2000076082679.
  3. Huang, Xingzhong. Active vortex control with moveable jet. USP2003126668638.
  4. Taylor Robert M. (Vienna VA). Aerodynamic surface tip vortex attenuation system. USP1992105158251.
  5. Smith David M. ; Dorris ; III John. Aircraft engine apparatus with reduced inlet vortex. USP2000106129309.
  6. Okinaga Tomioka JP. Aircraft installed snow remover. USP2002046378807.
  7. Johnstone Edmund H. (82 Salzburg Blvd. Apt. G Columbus IN 47201). Aircraft wing vortex deflector. USP1976083974986.
  8. Roland Stuff DE; Heinrich Vollmers DE. Aircraft with means for a premature breakdown of the wing vortex pair. USP2002076422518.
  9. Haney William R.. Airfoil vortex attenuation apparatus and method. USP1998095806807.
  10. Shmilovich,Arvin; Yadlin,Yoram; Clark,Roger; Leopold,Donald. Apparatus and method for the control of trailing wake flows. USP2006097100875.
  11. McFadden Russell E. (Andale KS) Shure ; III Charles H. (Haysville KS). Attached jet spanwise blowing lift augmentation system. USP1989084860976.
  12. Glezer, Ari; Crittenden, Thomas M.. Combustion-driven jet actuator. USP2003046554607.
  13. Schmidt Robert N. ; Shaw Greg S.. Fluid flow control devices. USP1998055755408.
  14. Ahmed A. Hassan ; David B. Domzalski. Jet actuators for aerodynamic surfaces. USP2002106471477.
  15. Nosenchuck Daniel M. (Mercerville NJ) Brown Garry L. (Princeton NJ). Lifting body with reduced-strength trailing vortices. USP1996025492289.
  16. Hieu T. Ngo ; Lisa E. Barlow. Lifting surface with active variable tip member and method for influencing lifting surface behavior therewith. USP2002056394397.
  17. Erwin John R. (Paradise Valley AZ). Method and apparatus for controlling tip vortices. USP1976123997132.
  18. Saddoughi, Seyed Gholamali; Leyva, Ivett Alejandra; Dean, Anthony John; Robic, Bernard Francois; Butler, Lawrence. Method and apparatus for modulating airfoil lift. USP2003106629674.
  19. Huenecke, Klaus. Method and apparatus for reducing trailing vortices in the wake of an aircraft. USP2003026513761.
  20. Glezer Ari ; Smith Barton L. ; Trautman Mark A.. Modifications of fluid flow about bodies and surfaces with synthetic jet actuators. USP1999095957413.
  21. Domzalski David B. ; Hassan Ahmed A. ; Kennedy Dennis K.. Oscillating air jets on aerodynamic surfaces. USP1999085938404.
  22. Powell,Arthur Gregory. Oscillating vane actuator apparatus and method for active flow control. USP2006097104143.
  23. James E. Smith ; John L. Loth ; Robert P. M. Craven ; Robert Bond. Piezoelectric actuators for circulation controlled rotorcraft. USP2002076425553.
  24. Glezer Ari ; Allen Mark G. ; Coe David J. ; Smith Barton L. ; Trautman Mark A. ; Wiltse John W.. Synthetic jet actuator and applications thereof. USP1998065758823.
  25. Glezer Ari ; Allen Mark G.. Synthetic jet actuators for cooling heated bodies and environments. USP2000096123145.
  26. Glezer Ari ; Smith Barton L.. Synthetic jet actuators for modifiying the direction of fluid flows. USP1999115988522.
  27. McCarthy Peter T. (134 Park St. #5 Buffalo NY 14201). Tip vortex generation technology for creating a lift enhancing and drag reducing upwash effect. USP1997065634613.
  28. Remington Paul J. ; Coney William B. ; Curtis Alan Robert Douglas. Use of flow injection and extraction to control blade vortex interaction and high speed impulsive noise in helicopters. USP2001096283406.
  29. Griswold ; II Roger W. (Ben Franklin Rd. Old Lyme CT 06371). Vortex alleviating wing tip. USP1984104477042.
  30. Yuan Shao Wen (2021 Highboro Way Falls Church VA 22043). Vortex control. USP1976023936013.
  31. Gutmark Ephraim J. ; Guillot Stephen A.. Vortical lift control over a highly swept wing. USP2000106138955.
  32. Yasuisa Ooga JP. Wake turbulence detecting system. USP2002076424408.
  33. Ransick Thomas F. (Rockford IL). Wingtip turbine. USP1992095150859.
  34. Patterson ; Jr. James C. (Yorktown VA). Wingtip vortex dissipator for aircraft. USP1976103984070.
  35. Gerhardt Heinz Adolf. Wingtip vortex impeller device for reducing drag and vortex cancellation. USP1999075918835.