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특허 상세정보

Supersonic aircraft with spike for controlling and reducing sonic boom

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-030/00    B64C-007/00   
미국특허분류(USC) 244/001.N; 244/119; 181/211
출원번호 US-0104403 (2002-03-22)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Howrey Simon Arnold & White LLP
인용정보 피인용 횟수 : 24  인용 특허 : 63
초록

An aircraft includes a spike projecting forward from the leading end of the fuselage and/or rearward from the trailing end of the fuselage. The spike can include a single section or two or more sections of varying cross-sectional area. Transition regions between sections of varying cross-sectional area are located and shaped to reduce coalescence of shock waves created thereby during supersonic flight. The spike can be collapsible and can be retracted into the fuselage. The spike can have a cross-sectional shape wherein the nose thereof lies on a line fo...

대표
청구항

An aircraft includes a spike projecting forward from the leading end of the fuselage and/or rearward from the trailing end of the fuselage. The spike can include a single section or two or more sections of varying cross-sectional area. Transition regions between sections of varying cross-sectional area are located and shaped to reduce coalescence of shock waves created thereby during supersonic flight. The spike can be collapsible and can be retracted into the fuselage. The spike can have a cross-sectional shape wherein the nose thereof lies on a line fo...

이 특허에 인용된 특허 (63)

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이 특허를 인용한 특허 피인용횟수: 24

  1. Kucherov, Yan R.; Hubler, Graham K.. Blast wave effects reduction system. USP2014028646373.
  2. Grip, Robert Erik; Brown, John Joseph. Expandable nose cone. USP2015099132908.
  3. Lugg, Richard H.. Hypersonic aircraft. USP20190310232937.
  4. Conners, Timothy R.; Henne, Preston A.; Howe, Donald C.. Isentropic compression inlet for supersonic aircraft. USP2016119482155.
  5. Conners, Timothy R.; Howe, Donald C.; Henne, Preston A.. Isentropic compression inlet for supersonic aircraft. USP2012128333076.
  6. Henne, Preston A.; Conners, Timothy R.; Howe, Donald C.. Isentropic compression inlet for supersonic aircraft. USP2012128327645.
  7. Henne, Preston A.; Conners, Timothy R.; Howe, Donald C.. Isentropic compression inlet for supersonic aircraft. USP2012108286434.
  8. Conners, Timothy R.. Low shock strength inlet. USP2013038393158.
  9. Conners, Timothy R.. Low shock strength inlet. USP2015059027583.
  10. Conners, Timothy R.. Low shock strength propulsion system. USP2014068739514.
  11. Conners, Timothy R.. Low shock strength propulsion system. USP2014078783039.
  12. Felter,John; Thacker,Michael; Laflin,Kelly. Method and system for gathering pressure signature data using a scaled model in a wind tunnel. USP2007127302839.
  13. Kobayashi,Hiroaki; Tanatsugu,Nobuhiro; Sato,Tetsuya; Hongo,Motoyuki; Maru,Yusuke. Method for reducing resistance of flying object using expandable nose cone. USP2006107118072.
  14. Morgenstern, John M.; Bach, James B.; Arslan, Alan E.. Methods for configuring aircraft to meet performance goals and shock wave disturbance constraints. USP2013068473254.
  15. Arata,Allen A.. Movable nose cap and control strut assembly for supersonic aircraft. USP2007107278609.
  16. Minick, Alan B.. Rotary wing system with ion field flow control. USP2012018091836.
  17. Henne, Preston A.; Howe, Donald C.; Wolz, Robert R.. Sub-scale sonic boom modeling. USP2009127634941.
  18. Henne, Preston A.; Conners, Timothy R.; Howe, Donald C.. Supersonic aircraft jet engine installation. USP2016059334801.
  19. Lugg, Richard H.. Supersonic aircraft with shockwave canceling aerodynamic configuration. USP2013068453961.
  20. Henne, Preston A.; Howe, Donald C.; Wolz, Robert R.; Hancock, Jr., Jimmy L.. Supersonic aircraft with spike for controlling and reducing sonic boom. USP2014078789789.
  21. Freund, Donald. Systems and methods for controlling a magnitude of a sonic boom. USP20181010093410.
  22. Freund, Donald. Systems and methods for controlling a magnitude of a sonic boom. USP2016099446839.
  23. Freund, Donald. Systems and methods for controlling a magnitude of a sonic boom. USP2017029561847.
  24. Freund, Donald. Systems and methods for controlling a magnitude of a sonic boom. USP2017029580169.