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특허 상세정보

Switchable vortex generator and array formed therewith, and uses of the same

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/00    B64C-003/38    F15D-001/12    G01M-009/04   
출원번호 US-0089992 (2013-11-26)
등록번호 US-9650124 (2017-05-16)
우선권정보 DE-10 2008 022 504 (2008-05-07)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Global IP Counselors, LLP
인용정보 피인용 횟수 : 0  인용 특허 : 17
초록

A vortex generator is useable in a model in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular, aircraft, to save wind tunnel time, it is suggested to configure the vortex generator to be switchable. A switchable vortex generator can be used, in particular, on models in fluid-dynamic channels and in fluid-dynamic channel tests.

대표
청구항

1. A vortex generator for generating vortices, the vortex generator comprising: a vortex generating element, switchable between at least two stable switching states, such that the vortex generating element maintains each stable switching state without energy input; anda bistable biasing component configured to contact the vortex generating element to enable switching of the vortex generating element between the stable switching states by an energy impulse. 2. The vortex generator according to claim 1, wherein the bistable biasing component comprises at l...

이 특허에 인용된 특허 (17)

  1. Alan J. Bilanin ; Robert M. McKillip, Jr.. Actuating device with at least three stable positions. USP2002026345792.
  2. McKillip ; Jr. Robert M.. Actuating device with multiple stable positions. USP2001046220550.
  3. Zell Peter T. (San Jose CA). Aerodynamic surface distension system for high angle of attack forebody vortex control. USP1994075326050.
  4. DiCocco,Jack; Prince,Troy; Patel,Mehul; Ng,Tsun Ming Terry. Aircraft and missile afterbody flow control device and method of controlling flow. USP2006077070144.
  5. Prince, Troy; Lisy, Frederick J.; Patel, Mehul P.; DiCocco, Jack M.; Carver, Reed; Schmidt, Robert N.. Aircraft and missile forebody flow control device and method of controlling flow. USP2004026685143.
  6. Prince, Troy; Lisy, Frederick J.; Patel, Mehul P.; DiCocco, Jack M.; Carver, Reed; Schmidt, Robert N.. Aircraft and missile forebody flow control device and method of controlling flow. USP2011077977615.
  7. Prince,Troy; Lisy,Frederick J.; Patel,Mehul P.; DiCocco,Jack M.; Carver,Reed; Schmidt,Robert N.. Aircraft and missile forebody flow control device and method of controlling flow. USP2007067226015.
  8. Wygnanski Israel,ILX ; Greenblatt David,ILX ; Seifert Avi,ILX. Airfoil with dynamic stall control by oscillatory forcing. USP2001076267331.
  9. van Namen, Frederik T.. Bistable electro-magnetic mechanical actuator. USP2003016512435.
  10. Lisy, Frederick J.; Modarreszadah, Mohammed; Patel, Mehul P.; DiCocco, Jack M.; Carver, Reed; Schmidt, Robert N.; Prince, Troy. Flow control device and method of controlling flow. USP2005016837465.
  11. Lisy,Frederick J.; Modarreszadah,Mohammed; Patel,Mehul P.; DiCocco,Jack M.; Carver,Reed; Schmidt,Robert N.; Prince,Troy. Flow control device and method of controlling flow. USP2008027334760.
  12. Wygnanski Israel (4559 N. Placita de las Charcras Tucson AZ 85718). Method and apparatus for delaying the separation of flow from a solid surface. USP1993055209438.
  13. Bauer Steven X. S. ; Wood Richard M.. Micro-drag generators for aerodynamic and hydrodynamic braking and control. USP2000106131853.
  14. Lee,Hak Tae; Bieniawski,Stefan R.; Kroo,Ilan M.. Miniature trailing edge effector for aerodynamic control. USP2008087410133.
  15. Lorkowski, Thomas; Grohmann, Boris. System for reducing aerodynamic noise at a supplementary wing of an aircraft. USP2010087766281.
  16. Lorkowski, Thomas; Grohmann, Boris. System for reducing aerodynamic noise at a supplementary wing of an aircraft. USP2011088006941.
  17. Waring John,CAX ITX K4A 3H5. Wearable article for athlete with vortex generators to reduce form drag. USP1998045734990.