$\require{mediawiki-texvc}$
  • 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

Low sonic boom inlet for supersonic aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64B-001/24    B64B-001/00   
미국특허분류(USC) 244/053.B; 137/015.1
출원번호 US-0966551 (2001-09-26)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Calfee, Halter &
인용정보 피인용 횟수 : 40  인용 특허 : 6
초록

All-internal compression inlets for supersonic aircraft, with variable geometry systems and shock stability bleed systems provide high performance, large operability margins, i.e. terminal shock stability that reduces the probability of inlet unstart, and contribute little or nothing to the overall sonic boom signature of the aircraft. These inlets have very high internal area contraction or compression and very low external surface angles. All shocks from the internal inlet surfaces are captured and reflected inside the inlet duct, and all of the exte...

대표
청구항

We claim: 1. A supersonic inlet for use with an aircraft, said supersonic inlet comprising: an internal duct having an opening for receiving airflow and a throat section, said inlet further comprising one or more external surfaces wherein said one or more entire external surfaces are aligned with the flow of the aircraft, said opening of said internal duct further comprised of a first and second leading edge, wherein said leading edges are staggered in location; and said throat section of the inlet further incorporating a shock stability bleed system, ...

이 특허를 인용한 특허 피인용횟수: 40

  1. Rupp, George D.; Troia, Trajaen J.. Aircraft engine airflow modulation apparatus and method for engine bay cooling and cycle flow matching. USP2016059353684.
  2. Kucherov, Yan R.; Hubler, Graham K.. Blast wave effects reduction system. USP2014028646373.
  3. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  4. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  8. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  9. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  10. Conners, Timothy R.; Henne, Preston A.; Howe, Donald C.. Isentropic compression inlet for supersonic aircraft. USP2016119482155.
  11. Conners, Timothy R.; Howe, Donald C.; Henne, Preston A.. Isentropic compression inlet for supersonic aircraft. USP2012128333076.
  12. Henne, Preston A.; Conners, Timothy R.; Howe, Donald C.. Isentropic compression inlet for supersonic aircraft. USP2012128327645.
  13. Henne, Preston A.; Conners, Timothy R.; Howe, Donald C.. Isentropic compression inlet for supersonic aircraft. USP2012108286434.
  14. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Low noise aeroengine inlet system. USP2018059957889.
  15. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Low noise aeroengine inlet system. USP2018049951690.
  16. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Low noise aeroengine inlet system. USP20180810054050.
  17. Conners, Timothy R.. Low shock strength inlet. USP2013038393158.
  18. Conners, Timothy R.. Low shock strength inlet. USP2015059027583.
  19. Conners, Timothy R.. Low shock strength propulsion system. USP2014068739514.
  20. Conners, Timothy R.. Low shock strength propulsion system. USP2015038973370.
  21. Conners, Timothy R.. Low shock strength propulsion system. USP2014078783039.
  22. Gutmark, Ephraim; Kastner, Jeffrey; Chapin, David Michael; Farmer, Terry Lewis; Shelton, James Knox. Method and systems for acoustic cleaning. USP2015038984714.
  23. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  24. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  25. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  26. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  27. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  28. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  29. Henne, Preston A.; Conners, Timothy R.; Howe, Donald C.. Supersonic aircraft jet engine installation. USP2016059334801.
  30. Henne, Preston A.; Howe, Donald C.; Wolz, Robert R.; Hancock, Jr., Jimmy L.. Supersonic aircraft with spike for controlling and reducing sonic boom. USP2014078789789.
  31. Baruzzini, Dan J.; Miller, Daniel N.; Domel, Neal D.; Hakes, Jeff G.. Suprression of shock-induced airflow separation. USP20180810054048.
  32. Leland, Bradley C.; Lundy, Brian F.; Klinge, John D.. System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines. USP2010047690595.
  33. dos Santos e Lucato, Sergio L.; Marshall, David B.; Driemeyer, Daniel Edward. Tailorable stiffness shape morphing flow-path. USP2013118590842.
  34. 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.
  35. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  36. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  37. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Variable geometry inlet system. USP20190310221764.
  38. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  39. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.
  40. Huynh, Thuy. Variable-geometry rotating spiral cone engine inlet compression system and method. USP2014048690097.