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Aircraft boundary layer control system with discharge transpiration panel

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/209 ; 244/207 ; 244/208 ; 244/130
출원번호 US-0566584 (1995-11-30)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Christensen O'Connor Johnson & Kindness PLLC
인용정보 피인용 횟수 : 18  인용 특허 : 3
초록
▼

An improvement to boundary layer control system, including a transpiration panel (58) for transpiring suction air in a distributed manner, is provided. The transpiration panel (58) replaces the discharge nozzle of prior art flow control systems. The transpiration panel (58) is generally a rigid panel having a plurality of small holes (62) extending from an inner panel surface (56) to a smooth outer panel surface (54). The transpiration panel (58) is positioned flush with an external aircraft surface in a region where laminar flow control is not being att...

대표
청구항
▼

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] In a boundary layer flow control system for an aircraft including a perforated suction region, a compressor, and inlet ducting for passing suction air from the suction region to the compressor, the improvement comprising a transpiration panel coupled to the output of the compressor, the transpiration panel being located in a surface of the aircraft other than an aircraft wing outboard chordwise surface, in regions where aerodynamic flow...

이 특허에 인용된 특허 (3)

  1. Cook Leonard J. (Canoga Park CA) Rosenthal Herman A. (San Diego CA). Aircraft anti-icing plenum. USP1976013933327.
  2. Rethorst Scott Carson (South Pasadena CA). Compression energy transformation system for a supersonic wing. USP1977024008866.
  3. Lurz Werner (Hamburg DEX). Method for stabilizing laminar separated boundary layers. USP1987054664345.

이 특허를 인용한 특허 피인용횟수: 18

  1. Lorkowski, Thomas. Aerodynamic body and high-lift system comprising such an aerodynamic body. USP2013048408498.
  2. Willdig, Victor John; Sharp, Kim. Aircraft cooling duct. USP2015028960601.
  3. Wainfan Barnaby Sam ; Liu Yu Ping ; Rihn Daniel R. ; Leggett Douglas William ; Georges Martin James ; Philhower Jeffry Scott ; Shultz Douglas Ellwood ; Boccados Charles. Aircraft engine air intake system. USP2000106138950.
  4. Carr,Robert Jonathan; Higgins,James Michael. Aircraft internal wing and design. USP2007087258302.
  5. Schwarz, Frederick M.. Aircraft thermal management system with reduced exhaust re-ingestion. USP2010127857257.
  6. Collett Edward,GBX. Aircraft wing leading edge high lift device with suction. USP2000106135395.
  7. Shmilovich, Arvin; Yadlin, Yoram. Aircraft wing structure and associated method for addressing lift and drag. USP20181010099771.
  8. Saari, Aapo; Kapiainen, Tomi; Heikkinen, Kim; Laurila, Jussi; Löfberg, Niklas; Rauta, Visa; Mäkelä, Klaus; Hitunen, Jussi; Salonen, Tommi; Bergman, Kim; Parkkinen, Jarmo. Control panel. USP201607D760611.
  9. Williams, Stewart W; Turner, Brian J. Laminar flow control system and suction panel for use therewith. USP2004066752358.
  10. Meyer,Pascal J. Laminar flow nacelle for an aircraft engine. USP2006057048230.
  11. Loth Eric. Mesoflap passive transpiration system and method for shock/boundary layer interaction control. USP1999105971327.
  12. Morgenstern,John M.; Arslan,Alan E.; Moose,Garret A.. Methods for incorporating area ruled surfaces in a supersonic aircraft. USP2007127311287.
  13. Al-Garni, Ahmed Z.; Al-Qutub, Amro M.. Movable surface plane. USP2003096622973.
  14. Atassi, Oliver V.. Nacelle with porous surfaces. USP2015038974177.
  15. Booher, Sr., Benjamin V.. Parasitic drag induced boundary layer reduction system and method. USP2017079701399.
  16. Tiwari, Sean; Weaver, Luby. Perforated surface for suction-type laminar flow control. USP20180610000277.
  17. Meister Juergen,DEX ; Pfennig Juergen,DEX ; Held Werner,DEX. Rudder assembly with a controlled boundary layer control for an aircraft. USP1999055899416.
  18. Richardson, John. System and method for cooling an aircraft wing. USP2016099452841.

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