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특허 상세정보

Mission adaptive inlet

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-033/02   
미국특허분류(USC) 244/053B ; 137/015.1
출원번호 US-0549457 (2000-04-14)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Harness Dickey & Pierce P.L.C.
인용정보 피인용 횟수 : 27  인용 특허 : 2
초록

A mission adaptive inlet (42) for an aircraft (40) has a rigid lip panel (56) pivotally attached to an inlet (42) of the aircraft (40). An actuation mechanism is coupled to the rigid lip panel (56) and causes the rigid lip panel (56) to pivot from a first position to a second position. A reinforced elastomer system (48) is connected the rigid lip panel and the inlet (42).

대표
청구항

[ What is claimed is:] [1.]1. An aircraft having a mission adaptive inlet for controlling airflow into a jet engine of the aircraft, comprising:a nacelle attached to an aircraft;a plurality of rigid lip segments pivotally attached to the nacelle; anda plurality of reinforced elastomer lip segments connected between two of the plurality of rigid lip segments, the reinforced elastomer lip segments being movable to control airflow into the engine without forming gaps or discontinuities in a surface of the nacelle.

이 특허를 인용한 특허 피인용횟수: 27

  1. Clark, Daniel; Webster, John R. Actuator. USP2011108043045.
  2. Shammoh, Ali A. A. J.. Adjustable angle inlet for turbojet engines. USP2013108544793.
  3. Sakurai, Seiya; Fox, Stephen J.; Grimlund, Kristin E.. Apparatus and methods for varying inlet lip geometry of a jet engine inlet. USP2005066910327.
  4. Dunne, James P.; Pitt, Dale M.; Kilian, Kevin J.; White, Edward V.. Apparatus for variation of a wall skin. USP2003076588709.
  5. Marengo, Giovanni Antonio. Composite flange, duct incorporating a flange and method of making a flange. USP2013038393648.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  9. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath. USP2016059328662.
  10. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath and design method thereof. USP2015038985507.
  11. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  12. Eveker, James V.; Young, Roger K.. Hinge cover integration into door seal edges. USP2009087575195.
  13. Eveker, James V.; Young, Roger K.. Hinge cover integration into door seal edges. USP2005046877695.
  14. Eveker, James V.; Young, Roger K.. Hinge cover integration into door seal edges. USP2012028108980.
  15. Howarth, Graham; Calder, David P.. Integrated inlet design. USP2012048152461.
  16. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  17. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  18. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  19. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  20. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  21. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  22. Sankrithi, Mithra M. K. V.; Nelson, Paul E.. Rotatable scarf inlet for an aircraft engine and method of using the same. USP2004076764043.
  23. Entsminger, Adam; Bouldin, Bruce Dan. UAV ducted fan lip shaping. USP2012088240597.
  24. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  25. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.
  26. Porte, Alain; Prat, Damien. Ventilating air intake arrangement. USP2013048425283.
  27. Porte, Alain; Prat, Damien. Ventilating air intake arrangement with mobile closing device. USP2014028651925.