• 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

Reconfigurable porous technology for fluid flow control and method of controlling flow

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/02   
미국특허분류(USC) 244/204; 244/209; 244/210
출원번호 US-0336113 (2003-01-03)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 12  인용 특허 : 11

The present invention relates to a reconfigurable porous technology for fluid flow control system and more particularly to reconfigurable porosity fluid flow control system for vehicles such as aircraft, missiles, ground and water vehicles to improve the performance of such vehicles. The present invention further relates to a method of operating the reconfigurable fluid flow control system.In one embodiment, the present invention includes a reconfigurable porosity system for fluid flow control on the surface of an aircraft, missile, water-craft or ground...


1. A reconfigurable porosity system for fluid flow control on the surface of an aircraft missile, watercraft or ground vehicle comprisinga porous outer skin comprising individual pores; individually addressable valves corresponding and connected individual pores for opening and closing the pores; a pneumatic system for connecting the pores; a sensor having an output, the output being used at least in part to estimate or determine the high and low pressure areas of the porous outer skin, and a closed loop control system far opening and closing the individ...

이 특허에 인용된 특허 (11)

  1. Bohning Rainer (Karlsruhe DEX). Aircraft wing having a super critical profile and a venting device for reducing compression shock. USP1994085335885.
  2. O'Neil Patrick J.. Airfoil lift management device. USP1998095806808.
  3. Anxionnaz Rene (8 ; RUE Nicolas Chuquet 75-Paris FR). Device for regulating and recovering the boundary layer over the surface of a body such as an aircraft in flight. USP1976043951360.
  4. Viets Hermann (144 Scenery Dr. Morgantown WV 26505). Directional control of engine exhaust thrust vector in a STOL-type aircraft. USP1983074392621.
  5. Meier Hans U. (Gttingen DEX) Maier Alois (Gttingen DEX) de Zhou Ming (Nanjing CNX). Method and apparatus for influencing a laminar turbulent boundary layer transition on bodies in flow. USP1991024989810.
  6. DeCoux Steven P. (Long Beach CA). Method and apparatus for laminar flow control. USP1994055316032.
  7. Lurz Werner (Hamburg DEX). Method for stabilizing laminar separated boundary layers. USP1987054664345.
  8. Marc A. Unger ; Hou-Pu Chou ; Todd A. Thorsen ; Axel Scherer ; Stephen R. Quake. Microfabricated elastomeric valve and pump systems. USP2002066408878.
  9. Barnwell Richard (Newport News VA) Bushnell Dennis (Wicomico VA) Nagamatsu Henry T. (Schenectady NY) Bahi Lakhdar (Troy NY) Ross Janet (Burbank CA). Passive drag control of airfoils at transonic speeds. USP1985064522360.
  10. O'Neil Patrick J. ; Billman Garrett M.. Passive porosity airfoil management device. USP2000066079671.
  11. Ng T. Terry. Vortex generation for control of the air flow along the surface of an airfoil. USP2001106302360.