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특허 상세정보

Variable camber inlet for supersonic aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02   
미국특허분류(USC) 244/53B ; 137/151 ; 244/44
출원번호 US-0655329 (1976-02-05)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 28  인용 특허 : 0
초록

An inlet for a supersonic aircraft capable of varying capture area. The inlet is of a rectangular shape, and has a ramp attached to the top and bottom of its fore end. The ramps are positioned to maximize air capture area during supersonic flight. At subsonic speeds, the ramps are moved to a position which slightly reduces the capture area. The ramps may have a blunt edge or sharp edge, and are controlled by an actuator located within the aircraft and connected to the ramps by suitable linkage. The ramps have a smooth contour provided by a flexible outer...

대표
청구항

In a rectangular cross sectioned air inlet for an engine operatively associated with a supersonic aircraft, the air inlet having an outer surface exposed to ambient air and an inner surface forming the primary passageway for intake of air to the engine, and means for varying the capture area of the primary passageway comprising, a. a first ramp mounted to the top forward edge of the inlet, said first ramp having three portions, a fore portion, a middle portion, and an aft portion, the fore portion pivotally mounted to the middle portion, the middle porti...

이 특허를 인용한 특허 피인용횟수: 28

  1. Frost Richard C. (Fort Worth TX) Gomez Eduardo W. (Fort Worth TX) McAnally Robert W. (Fort Worth TX). Airfoil variable cambering device and method. USP1981014247066.
  2. Sakurai, Seiya; Fox, Stephen J.; Grimlund, Kristin E.. Apparatus and methods for varying inlet lip geometry of a jet engine inlet. USP2005066910327.
  3. Gruensfelder Cynthia Ann. Auxiliary inlet for a jet engine. USP2000066079667.
  4. Statkus Frank D. (Woodinville WA). Continuous skin, variable camber airfoil edge actuating mechanism. USP1982094351502.
  5. Eppler Richard (Leibnizstrasse 84 7000 Stuttgart 1 DEX). Device to support rudders and trailing edge flaps of aircraft and watercraft. USP1980104230295.
  6. Tindell Runyon H. (Old Bethpage NY). Flight control augmentation inlet device. USP1990124979699.
  7. Adamson, Eric E; Fugal, Spencer Robert. Flow inlet. USP2018029896219.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  9. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  10. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  11. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath. USP2016059328662.
  12. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath and design method thereof. USP2015038985507.
  13. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  14. Gruensfelder Cynthia Ann ; Brase ; Jr. Lawrence O.. Leading edge for an aircraft. USP2001046213433.
  15. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2000076089505.
  16. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2001076260567.
  17. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  18. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  19. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  20. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  21. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  22. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  23. Strom Thomas H. (Newport News VA 4). Superagile tactical fighter aircraft and method of flying it in supernormal flight. USP1990014896846.
  24. Grip, Robert E.; Brown, John J.. Two-surface sandwich structure for accommodating in-plane expansion of one of the surfaces relative to the opposing surface. USP2017019555871.
  25. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  26. Lamb, Jr., Donald William. Variable geometry helicopter engine inlet. USP2017059656760.
  27. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.
  28. Santini, Gregory M.. Wing variable camber trailing edge tip. USP2014098844879.