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특허 상세정보

Rocket motor nozzle throat area control system and method

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B63H-011/00   
미국특허분류(USC) 060/204; 060/253; 239/265.19
출원번호 US-0880858 (2004-06-29)
등록번호 US-7464535 (2008-12-16)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Ingrassia, Fisher & Lorenz, P.C.
인용정보 피인용 횟수 : 0  인용 특허 : 14
초록

A solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cross sectional flow area. Controlling the effective cross sectional flow area of the nozzle throat in turn controls combustion chamber pressure, thus the burn rate of the propellant in the combustion chamber, and thus the thrust generated thereby.

대표
청구항

We claim: 1. A rocket motor, comprising: a motor having an inner surface defining a combustion chamber, the combustion chamber configured to receive a propellant therein and supply combustion gas upon ignition of the propellant; a nozzle including at least an inlet section, a primary throat, and an outlet section fluidly coupled in flow-series, the nozzle inlet section in fluid communication with the combustion chamber and including an inner surface defining a nozzle inlet passage having a convergent cross sectional flow area, the nozzle outlet section ...

이 특허에 인용된 특허 (14)

  1. Lee, Douglas; Anderson, J. Thomas; Hershberger, Brian K.. Apparatus and method for controlling primary fluid flow using secondary fluid flow injection. USP2004016679048.
  2. McDonald Allan J. (Brigham City UT). Combination diffuser, thermal barrier, and interchamber valve for rockets. USP1977054023355.
  3. Lawrence William J. (San Jose CA) Stolan John A. (San Jose CA) Leisch Steven O. (Morgan Hill CA). Electronic valve control for gas generator outflow. USP1992125172547.
  4. Herbert Stephen Jones ; Joseph Paul Arves ; Darren Andrew Kearney ; Ryan Earl Roberts ; Rory Nell McLeod. Hybrid injection thrust vector control. USP2002036354074.
  5. Le Tanter Grard (Castelnau Medoc FRX) Luscan Bernard (Merignac FRX). Integral booster/ramjet drive. USP1986124631916.
  6. Shumate,James. Method and apparatus for thrust augmentation for rocket nozzles. USP2006016983587.
  7. Abbott Adrian (Southampton GB2). Method of and system for controlling a fluidic valve. USP1989044819431.
  8. Chang Franklin R. (Webster TX). Method of hybrid plume plasma propulsion. USP1990014893470.
  9. Singer Victor (Newark DE) Kerrigan Barry E. (Newark DE). Rocket propelled vehicle forward end control method and apparatus. USP1989044819426.
  10. Knapp Raymond (Sacramento CA) Woodruff Robert (Carmichael CA). Self-actuating control for rocket motor nozzle. USP1996025491973.
  11. Keirsey James L. (Silver Spring MD). Solid fuel ramjet flow control device. USP1986124628688.
  12. Johnston Ian M.,GB2 ; Gill Raymond C.,GB2. Solid propellant combustion apparatus. USP1998095808231.
  13. Singer Victor (Newark DE) Lushis Donald V. (Newark DE) Kirschner ; Jr. Thomas J. (North East MD). Thrust reversal system. USP1984114484439.
  14. Bell, Frank H.. Variable aperture annular nozzle for rocket motor igniter. USP1983044378674.