• 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Linear shock wave absorber

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-001/40    B64C-001/00    B64C-023/00    B64C-009/16    B64C-009/00    B64C-001/38   
미국특허분류(USC) 244/001.N; 244/210; 244/130; 244/211; 244/123.1; 244/207
출원번호 US-0063314 (2005-02-21)
등록번호 US-7357351 (2008-04-15)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 1  인용 특허 : 16

A linear cavity is provided on the leading edge of an object that is subject to the flow of liquids or gasses, where said cavity preferably has a wall that follows the curvature of a diminishing sine wave, although other configurations are possible that do not follow a specific sine wave. The cavity accepts the flow of liquids or gasses that enter into the cavity, and where the dimensions of the cavity cause the flow of liquids or gases within it to form a pressure node that extends forward of the cavity. The pressure node provides a wedge means to cause...


I claim: 1. A leading edge, where said leading edge defines a linear structure said leading edge comprises a primary cavity extending along the entire length of the leading edge, said primary cavity defined by a first mouth comprising an upper and lower lip opening onto the leading edge and a first inner side wall; said primary cavity has a depth or width that exceeds the width of the first mouth; said first inner side wall comprises a second mouth defined on the back rear side; said second mouth leads to a secondary cavity having a second inner sidewal...

이 특허에 인용된 특허 (16)

  1. Bushman Boyd B.. Airfoil leading edge with cavity. USP1998115836549.
  2. Loebert Gerhard (Baldham DEX). Apparatus for reducing turbulent drag. USP1988044736912.
  3. Munroe Ronald G. (P.O. Box 317 Georgetown SC 29440). Automatic leading edge slat for aircraft. USP1983124422606.
  4. Grose Ronald D. (Omaha NE). Cascaded micro-groove aerodynamic drag reducer. USP1987034650138.
  5. Grose Ronald D. (61 Hwy. 211 Newport WA 99156). Cascaded turbulence generation inhibitor. USP1988074759516.
  6. Byron David E. (Casselberry FL). Cooling method and apparatus for wings and other fuselage components. USP1990104962903.
  7. Doria Iriarte JosJ. (Rodrguez Arias ; 61-10 48013 Bilbao (Vizcaya) ESX). Fairing for obtaining steady stabilization effects. USP1995095449136.
  8. Ferguson, Stanley D.; Eastman, Donald W.. High performance submerged air inlet. USP1983034378097.
  9. Stephen M. Ruffin. Leading edge channel for enhancement of lift/drag ratio and reduction of sonic boom. USP2002106464171.
  10. Kraenzien Peter,DEX. Leading edge construction for an aerodynamic surface and method of making the same. USP2000046050523.
  11. Morenus Richard C. (Long Beach CA) Frazer Alson C. (Santa Ana CA). Ram air combustion steering system for a guided missile. USP1986034573648.
  12. Bains William R. (Lake Elsinore CA) Sumrall Calhoun W. (Irvine CA). Ram air steering system for a guided missile. USP1985064522357.
  13. Schmidt, Eric T.. Shock wave absorber. USP2005026857604.
  14. Cunningham ; Jr. Atlee Marion. Trapped vortex airfoil nose. USP2000126161802.
  15. Hirschel Ernst H. (Zorneding DEX) Fleckenstein Hubert (Grasbrunn DEX) Thiede Peter (Ganderkesee DEX). Wall with a drag reducing surface and method for making such a wall. USP1990034907765.
  16. Evans Arthur (Seattle WA). Wing leading edge slat. USP1983084399970.