$\require{mediawiki-texvc}$
  • 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

Surface plasma discharge for controlling leading edge contamination and crossflow instabilities for laminar flow

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/00   
미국특허분류(USC) 244/205; 244/130
출원번호 US-0406940 (2003-04-03)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 32  인용 특허 : 14
초록

The present invention provides a system and method for controlling leading edge contamination and crossflow instabilities for laminar flow on aircraft airfoils that is lightweight, low power, economical and reliable. Plasma surface discharges supply volumetric heating of the supersonic boundary layers to control the Poll Reynolds number and the cross flow Reynolds number and delay transition to turbulent flow associated with the leading edge contamination and crossflow instabilities. A closed-loop feedback control system that incorporates these principle...

대표
청구항

1. An aircraft, comprising:an airfoil having a leading edge, whereby air flow interacts with the leading edge to create a first boundary layer, characterized by a Poll Reynolds number, along an attachment line and a second boundary layer, characterized by a cross flow Reynolds number, along diverging streamlines, andplasma discharge elements distributed along the attachment line, said plasma discharge elements being adapted to generate a plasma to volumetrically heat the first and second boundary layers, thereby maintaining the Poll Reynolds number below...

이 특허에 인용된 특허 (14)

  1. Zenon Szulyk ; Brian Dyra ; Alex Makhlin. Dual input servo coupled control sticks. USP2002106459228.
  2. Carpenter Donald G. (Box 62 A North Granby CT 06060). Electrical technique. USP1977034014168.
  3. Rodgers Leonard J,GBX. Ice protection for porous structure. USP1999085944287.
  4. Saeks Richard E ; Kunhardt Erich E ; Carlton Lindley A ; Pap Robert M. Ion doping apparatus and method for aerodynamic flow control. USP2001066247671.
  5. Gratzer Louis B. (Seattle WA). Laminar flow control airfoil. USP1989034813631.
  6. Gerhardt Heinz Adolf ; Kerswell James Franklin ; Priestley Richard Thomas ; Gibson Berry Thomas. Laminar supersonic transport aircraft. USP1998125842666.
  7. Stack John P. (Yorktown VA) Mangalam Sivaramakrishnan M. (Hampton VA). Method and apparatus for detecting laminar flow separation and reattachment. USP1990064936146.
  8. Crouch Jeffrey D. ; Ng Lian L.. Method and apparatus using localized heating for laminar flow. USP2000026027078.
  9. Alla Ohliger ; Mahendra Maheshwari ; Joe Franklin Spangler. Method for fabrication of perforated composite. USP2002096451241.
  10. Miller, Paul A.; Aragon, Ben P.. Method for generating surface plasma. USP2003056570333.
  11. Mihora Dennis J. (Santa Barbara CA) Cannon Walter E. (San Jose CA). Shock wave stabilization apparatus and method. USP1997125692709.
  12. Gerhardt Heinz A. (Redondo Beach CA). Supersonic natural laminar flow wing. USP1996075538201.
  13. Blackburn Ronald F. ; Warmkessel Barry M. ; Kawamoto Sonja M.. System for increasing the aerodynamic and hydrodynamic efficiency of a vehicle in motion. USP1998085797563.
  14. Hughes Kevin A. (San Diego CA) Shieh Chih F. (San Diego CA). Turbine engine nacelle laminar flow control arrangement. USP1994035297765.

이 특허를 인용한 특허 피인용횟수: 32

  1. DiCocco, Jack; Prince, Troy; Patel, Mehul; Ng, Tsun Ming Terry. Aircraft and missile afterbody flow control device and method of controlling flow. USP2012068191833.
  2. DiCocco,Jack; Prince,Troy; Patel,Mehul; Ng,Tsun Ming Terry. Aircraft and missile afterbody flow control device and method of controlling flow. USP2006077070144.
  3. Prince, Troy; Lisy, Frederick J.; Patel, Mehul P.; DiCocco, Jack M.; Carver, Reed; Schmidt, Robert N.. Aircraft and missile forebody flow control device and method of controlling flow. USP2011077977615.
  4. Lee, Ching Pang; Wadia, Aspi Rustom; Cherry, David Glenn; Han, Je Chin. Airfoil leading edge end wall vortex reducing plasma. USP2009127628585.
  5. Osborne, Bradley Alan; Wilson, Christopher Daniel. Airfoil trailing edge plasma flow control apparatus and method. USP2011087988101.
  6. Lee, Ching-Pang; Wadia, Aspi Rustom; Cherry, David Glenn; Han, Je-Chin. Downstream plasma shielded film cooling. USP2010047695241.
  7. Hansen, Craig M.; McClure, Paul D.; Macheret, Sergey. Dynamically controlled cross flow instability inhibiting assembly. USP2014018636254.
  8. Hobart, Stephen Alan; Kokan, Timothy S.; Minick, Alan B.; Massey, Frederic H.. Extended range projectile. USP2010117823510.
  9. Minick, Alan B.; Hobart, Stephen Alan; Widman, Frederick; Kokan, Timothy S.; Massey, Frederic H.. Guided projectile. USP2011027891298.
  10. Lugg, Richard H.. Hypersonic aircraft. USP20190310232937.
  11. Hagseth, Paul E.; McClure, Paul D.. Inlet electromagnetic flow control. USP2011017870720.
  12. Corke, Thomas C.; Spivey, Richard. Methods and apparatus for reducing drag via a plasma actuator. USP2012018091950.
  13. Ginn, Kerry B.; Jenkins, Stewart A.; Wells, David M.; McCallum, Brent N.. Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators. USP2013068453457.
  14. McClure, Paul D.; Chase, Charles J.. Over-wing traveling-wave axial flow plasma accelerator. USP2011088006939.
  15. Domel, Neal D.; Baruzzini, Dan J.; Miller, Daniel N.. Passive robust flow control micro device. USP2013038403271.
  16. McClure, Paul D.; Finley, Dennis B.; Macheret, Sergey. Plasma actuated vortex generators. USP2014128916795.
  17. Wood, Tommie L.; Corke, Thomas C.; Post, Martiqua. Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft. USP2012118308112.
  18. Lee, Ching-Pang; Wadia, Aspi Rustom; Cherry, David Glenn; Carson, Scott Michael. Plasma enhanced rapidly expanded gas turbine engine transition duct. USP2011017870719.
  19. McClure, Paul D.; Macheret, Sergey; Smith, Brian R.; Chankaya, Kurt M.. Plasma enhanced riblet. USP2012078220754.
  20. Lee, Ching-Pang; Wadia, Aspi Rustom; Cherry, David Glenn; Han, Je-Chin. Plasma lifted boundary layer gas turbine engine vane. USP2010087766599.
  21. Patel, Mehul; Corke, Thomas; Cain, Alan B.. Plasma optimized aerostructures for efficient flow control. USP2017019541106.
  22. Gupta, Anurag; Saddoughi, Seyed Gholamali. Reduction of tip vortex and wake interaction effects in energy and propulsion systems. USP2012078226047.
  23. Minick, Alan B.. Rotary wing system with ion field flow control. USP2012018091836.
  24. Enloe,Carl L.; McLaughlin,Thomas E.; Jumper,Eric J.; Corke,Thomas C.. Single dielectric barrier aerodynamic plasma actuation. USP2008067380756.
  25. Land, III, H. Bruce; Grossman, Kenneth R.; Cybyk, Bohdan Z.; VanWie, David M.. Solid state supersonic flow actuator and method of use. USP2011087988103.
  26. Corke, Thomas; Thomas, Flint; Shatzman, David; Wood, Tommie. System and method for aerodynamic flow control. USP2014028640995.
  27. Essenhigh, Katherine Anne; Tao, Fengfeng; Bennett, Grover Andrew; Boespflug, Matthew; Murray, Robert C.; Saddoughi, Seyed Gholani. System, apparatus, program product, and related methods for providing boundary layer flow control. USP2013098523115.
  28. Drouin, Jr., Donald V.; Schwimley, Scott Lee. Systems and methods for alleviating aircraft loads with plasma actuators. USP2016099446840.
  29. Silkey, Joseph S.; Smereczniak, Philip. Systems and methods for controlling flows with pulsed discharges. USP2014058727286.
  30. Paesano, Antonio; Thompson, Robert B.. Textured leading edge for aerospace and nautical structures. USP2016119482096.
  31. Scott,Simon J; Johnson,Graham A; Thornton,Edward. Turbulent flow drag reduction. USP2006067066431.
  32. Minick,Alan B.; Goldberg,Benjamin; Knauer,Larry. Wing enhancement through ion entrainment of media. USP2008087413149.