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특허 상세정보

Shock inducing pod for causing flow separation

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/04   
미국특허분류(USC) 244/198 ; 244/130 ; 244/200
출원번호 US-0695759 (1985-01-29)
국제출원번호 PCT/US82/01378 (1982-09-30)
§371/§102 date 19820930 (19820930)
국제공개번호 WO-8400949 (1984-03-15)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 16  인용 특허 : 7
초록

A wing-mounted pod for preventing an unstable increase in the pitching moment of a swept-wing aircraft due to increasing speed and angle of attack is disclosed. This invention is for use on a swept-wing aircraft of the type having a nonlinear, unstable increase in its pitching moment due to a loss of lift at the outboard wing above a predetermined angle of attack at high Mach numbers. For an aircraft having a single, strut-mounted engine on each wing, the pod is placed along the intersection of the upper surface of the wing and the inboard side of the en...

대표
청구항

In an aircraft of the type having a nonlinear, unstable increase in the pitching moment above a predetermined angle of attack for a predetermined aircraft speed, said aircraft having a wing with a leading edge and an upper surface, an improvement comprising: means located on said upper surface of said wing for forming a shock in the air flowing over the upper surface of said wing at said predetermined aircraft angle of attack of said wing and at an aircraft speed above a Mach number of approximately 0.6, said shock causing localized separation of the air...

이 특허를 인용한 특허 피인용횟수: 16

  1. Wood, Norman. Aerodynamic structure with asymmetrical shock bump. USP2018029896193.
  2. Wood, Norman. Aerodynamic structure with non-uniformly spaced shock bumps. USP2016059334045.
  3. Wood, Norman. Aerodynamic structure with series of shock bumps. USP2016109463870.
  4. Peter May DE. Aircraft airfoil with close-mounted engine and leading edge high lift system. USP2002046364254.
  5. Fol, Thierry; Defos, Marjorie. Aircraft comprising a device for reducing the induced drag. USP2012058167248.
  6. Lyons, Neil John. Aircraft fairing. USP2015059027883.
  7. Dantin, Stephanie; Fol, Thierry; Gerard, Ludovic; Jimenez, Philippe. Aircraft wing arrangement comprising an engine attachment pylon defining, in the forward region, a lateral airflow channel. USP2011088006931.
  8. Klimov, Valentin T.; Chernousov, Vladimir I.; Surinov, Roman T.. Airplane. USP201404D702622.
  9. Bonnaud, Cyril; Dantin, Stephanie; Defos, Marjorie; Fol, Thierry. Airplane engine pylon comprising at least one protruding element to generate a vortex of the airflow. USP2012058186619.
  10. Adamson, Eric E.; Treiber, David A.. Apparatus and method for reducing a sonic boom signature. USP20181010093411.
  11. Atinault, Olivier. Device for controlling a vortex trail generated by the oblong element of an aircraft bearing surface. USP2011017866608.
  12. Hutcheson, Florence V.; Brooks, Thomas F.. Flow disruption devices for the reduction of high lift system noise. USP20190410252792.
  13. Wood, Norman. Shock bump. USP2012118302912.
  14. Harrison, Neal A.; Dehaan, Mark; Vassberg, John C.; Sclafani, Anthony J.. Submerged vortex generator. USP2016059340281.
  15. Grove, Darren V.. Transonic flow shockwave position stabilizer. USP2003026513754.
  16. Vassberg, John Charles; Gregg, III, Robert D.. Variable trailing edge geometry and spanload control. USP2005016843452.