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특허 상세정보

Supersonic aircraft and method

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06    B64C-021/04   
미국특허분류(USC) 244/208 ; 244/204 ; 244/209 ; 244/35A
출원번호 US-0883590 (1992-05-13)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 26  인용 특허 : 0

A supersonic aircraft having highly swept subsonic leading edge portions of the wings provided with boundary layer control suction slots. When the airplane is operating at high angles of attack under circumstances where noise is objectionable, air is drawn in through the suction strips to alleviate separated air flow and substantially eliminate (or at least alleviate) vortices that would otherwise develop over the upper wing surface. This improves the L/D ratio and permits the engines to be at a lower power setting, thus alleviating noise. There are show...


A supersonic aircraft comprising: a. an airfoil having an upper surface and a highly swept subsonic leading edge portion which is arranged to develop at high angles of attack separated flow that develops into a vortex that travels over the upper surface of the airfoil; b. said leading edge portion having an outer surface and having at said outer surface a boundary layer control suction strip means extending along said leading edge portion; c. suction means to draw in outside air through said suction strip means; and d. said suction means being arranged a...

이 특허를 인용한 특허 피인용횟수: 26

  1. Schmidt, Peter. Active and passive boundary layer control for vehicle drag reduction. USP2014108870275.
  2. Schmidt, Peter. Active and passive boundary layer control for vehicle drag reduction. USP2015119193399.
  3. Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C.. Aircraft. USP201008D622653.
  4. Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C.. Aircraft configuration. USP2011098016233.
  5. Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C.; Lan, Justin. Aircraft configuration. USP2014018628040.
  6. Morgenstern, John M.; Arslan, Alan. Aircraft lift device for low sonic boom. USP2005086935592.
  7. Collett Edward,GBX. Aircraft wing leading edge high lift device with suction. USP2000106135395.
  8. Moore, Matthew D.; Boren, Kelly L.; Marques, Edward C.. Airplane configuration. USP2012018087607.
  9. Gaster, Micheal. Establishment of laminar boundary layer flow on an aerofoil body. USP2012058172185.
  10. Lugg, Richard H.. Hypersonic aircraft. USP20190310232937.
  11. Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.. Lift augmentation system and associated method. USP2011108033510.
  12. Geissler, Alban. Lift system intended for free-falling persons. USP2004026685135.
  13. Parikh, Pradip G.. Passive removal of suction air for laminar flow control, and associated systems and methods. USP2011017866609.
  14. Timar Thomas. Ram air drive laminar flow control system. USP1998075779196.
  15. Hoisington, Zachary C.. Reduced flow field velocity for a propulsor. USP20180810040559.
  16. Meister Juergen,DEX ; Pfennig Juergen,DEX ; Held Werner,DEX. Rudder assembly with a controlled boundary layer control for an aircraft. USP1999055899416.
  17. Gallagher, Edward J.; Rogers, Thomas H.. Subsonic swept fan blade. USP2017109790797.
  18. Rouleau, Bruce S.; Graham, David H.; Reynolds, Ross S.; Wainfan, Barnaby S.. Supersonic aircraft. USP200303D471854.
  19. Lugg, Richard H.. Supersonic aircraft with shockwave canceling aerodynamic configuration. USP2013068453961.
  20. Hartmann Tom ; Morgenstern John M. ; Sokol Daniel. Supersonic business jet. USP199911D417184.
  21. Richardson, John. System and method for cooling an aircraft wing. USP2016099452841.
  22. Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.; Manley, David J.. System for aerodynamic flows and associated method. USP2009127635107.
  23. Ross James C. ; Storms Bruce L.. Tip fence for reduction of lift-generated airframe noise. USP1998045738298.
  24. Fedorov Alexander V.,RUX ; Malmuth Norman D.. Use of absorbing walls for laminar flow control. USP1999035884871.
  25. Gazdzinski Robert F.. Vehicular boundary layer control system and method. USP2000056068328.
  26. Ng T. Terry. Vortex generation for control of the air flow along the surface of an airfoil. USP2001106302360.