$\require{mediawiki-texvc}$
  • 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

System for reducing aerodynamic noise at a supplementary wing of an aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-003/50   
미국특허분류(USC) 244/215; 244/198; 244/210; 244/213; 244/214; 244/216
출원번호 UP-0791367 (2005-11-09)
등록번호 US-7766281 (2010-08-24)
우선권정보 DE-10 2004 056 537(2004-11-23)
국제출원번호 PCT/DE2005/002003 (2005-11-09)
§371/§102 date 20071207 (20071207)
국제공개번호 WO06/056160 (2006-06-01)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Crowell & Moring LLP
인용정보 피인용 횟수 : 16  인용 특허 : 15
초록

A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which thr...

대표
청구항

The invention claimed is: 1. A system for reducing aerodynamic noise of a supplementary wing of an aircraft, comprising: a portion of the supplementary wing hinged to the main wing, extendable to open a gap region between the main wing and the supplementary wing; a separating surface movable into the gap region when the supplementary wing is extended, the separating surface extending at least partially along a separation flow line between a vortex flow region and a gap flow region of air flowing in the gap region between the supplementary wing and the m...

이 특허에 인용된 특허 (15)

  1. Eliahou-Niv Shaul,ILX ; Wygnanski Israel,ILX. Active flaperon assembly. USP2001066247670.
  2. Wolfgang Gleine DE; Knut Mau DE; Udo Carl DE. Aerodynamic noise reducing structure for aircraft wing slats. USP2002056394396.
  3. Jeffrey W. Moe. Aircraft wing and method for reducing airframe-generated noise. USP2002096454219.
  4. Bliesner Wayne T. (Snohomish WA) Wang Timothy (Bellevue WA) Stoner Ronald C. (Bellevue WA). Apparatus and method for aircraft wing stall control. USP1991105056741.
  5. Werner Dobrzynski DE; Burkhard Gehlhar DE. Auxiliary airfoil for aircraft main wings. USP2002106457680.
  6. Holtrop John W. (Ridgecrest CA). Electrohydraulic control system. USP1983124418610.
  7. Mau, Knut; Dobrzynski, Werner. Flexible airflow separator to reduce aerodynamic noise generated by a leading edge slat of an aircraft wing. USP2004096789769.
  8. Collins, Andrew J.. Flight control surface actuation system. USP2004086776376.
  9. Scott Howard Z.. Low power loss electro hydraulic actuator. USP2001046209825.
  10. Trikha, Arun K.. Method and apparatus for controlling aircraft devices with multiple actuators. USP2004066755375.
  11. Tsunoda Stanley I. ; Bohanon Thomas M. ; Horner Mervyn H. ; Woolf Lawrence D.. Method and apparatus for fabricating panels used for the active control of surface drag. USP2001046220549.
  12. Shatz Solomon (P.O. Box 523 Cupertino CA 94015). Movable sheet for laminar flow and deicing. USP1997015590854.
  13. Thomassey, Lionel. Pivoting power transmission unit with peripheral face toothed gearwheels of the face gear type. USP2004016676073.
  14. Gleine, Wolfgang; Mau, Knut; Carl, Udo. Pressure control system for a pressure-expandable displacement element. USP2003036536714.
  15. Dizdarevic Faruk. Slot forming segments and slot changing spoilers. USP2001126328265.

이 특허를 인용한 특허 피인용횟수: 16

  1. Turner, Travis L.; Kidd, Reggie T.; Lockard, David P; Khorrami, Mehdi R.; Streett, Craig L.; Weber, Douglas Leo. Autonomous slat-cove-filler device for reduction of aeroacoustic noise associated with aircraft systems. USP2016019242720.
  2. Hirai, Makoto; Maeda, Ichiro. High-lift device, wing, and noise reduction structure for high-lift device. USP2013068469316.
  3. Hirai, Makoto; Maeda, Ichiro. High-lift device, wing, and noise reduction structure for high-lift device. USP2015049010692.
  4. Brown, James; Kay, Edmund. Krueger. USP2014028657239.
  5. Pitt, Dale M.; Eckstein, Nicholas Stephen. Method and apparatus for a leading edge slat on a wing of an aircraft. USP2013098534610.
  6. Pitt, Dale M.; Eckstein, Nicholas Stephen. Method for a leading edge slat on a wing of an aircraft. USP2016099446836.
  7. Vail, III, William Banning; Skerl, Tomislav. Methods and apparatus for monitoring and fixing holes in composite aircraft. USP2017039586699.
  8. Vail, III, William Banning. Methods and apparatus to prevent failures of fiber-reinforced composite materials under compressive stresses caused by fluids and gases invading microfractures in the materials. USP2017049625361.
  9. Pitt, Dale M.; Eckstein, Nicholas Stephen. Moveable leading edge device for a wing. USP2013098534611.
  10. Turner, Travis L.; Khorrami, Mehdi R.; Lockard, David P.; McKenney, Martin J.; Atherley, Raymond D.; Kidd, Reggie T.. Multi-element airfoil system. USP2014078763958.
  11. Hodkisson, Mark; Wilson, James; Evans, Samuel. Retractable infill panel for high-lift device. USP2016029254927.
  12. Havar, Tamas; Meyer, Oliver; Roth, York C.; Seack, Oliver. Slats with a flexible trailing edge. USP2013128596585.
  13. Gandhi, Umesh N.; Roe, Robert W.. Stackable wing for an aerocar. USP2015129216814.
  14. Gandhi, Umesh N.; Roe, Robert W.. Stackable wing for an aerocar. USP2017029580167.
  15. Neitzke, Klaus-Peter; Bauer, Karin; Bolzmacher, Christian; Kupke, Winfried. Switchable vortex generator and array formed therewith, and uses of the same. USP2017059650124.
  16. Neitzke, Klaus-Peter; Bauer, Karin; Bolzmacher, Christian; Kupke, Winfried. Switchable vortex generator and array formed therewith, and uses of the same. USP2013128616494.