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특허 상세정보

Flame holder for a hybrid rocket motor

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-009/28   
미국특허분류(USC) 060/251; 060/257; 060/253
출원번호 US-0054097 (2002-01-22)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Gordon & Jacobson, P.C.
인용정보 피인용 횟수 : 3  인용 특허 : 18
초록

A flame holder is provided at a head end of a combustion chamber of a hybrid rocket motor. The flame holder includes a high-temperature casing defining a cavity, and a solid propellant within cavity around or near the injector. The propellant may be provided in an annulus within the casing, such that the flame plume from the burning propellant is substantially parallel to the flow of the oxidizer, or may be generally cylindrical within a cylindrical casing such that the flame plume of the burning propellant is substantially perpendicular to the oxidizer ...

대표
청구항

A flame holder is provided at a head end of a combustion chamber of a hybrid rocket motor. The flame holder includes a high-temperature casing defining a cavity, and a solid propellant within cavity around or near the injector. The propellant may be provided in an annulus within the casing, such that the flame plume from the burning propellant is substantially parallel to the flow of the oxidizer, or may be generally cylindrical within a cylindrical casing such that the flame plume of the burning propellant is substantially perpendicular to the oxidizer ...

이 특허에 인용된 특허 (18)

  1. Bradford Michael D. (Santa Maria CA) McKinney Bevin C. (Ventura CA). Embedded pressurization system for hybrid rocket motor. USP1992065119627.
  2. Wagner William R. (Los Angeles CA). Expander-cycle, turbine-drive, regenerative rocket engine. USP1986044583362.
  3. Jones H. Stephen. Hybrid helium heater pressurization system and electrical ignition system for pressure-fed hybrid rockets. USP1998035722232.
  4. Bradford Michael D. (4896 Kenneth Ave. Santa Maria CA 93455) Kniffen ; Jr. Roy J. (934 Sharon La. ; #1 Ventura CA 93001) McKinney Bevin C. (252 N. Crimea Ventura CA 93004). Hybrid rocket combustion enhancement. USP1996125582001.
  5. Rolf E. Hamke ; Eric M. Rohrbaugh. Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines. USP2002056393830.
  6. Smith Kevin W. ; Kline Korey R. ; Slack ; Jr. Theodore C. ; Mossberg Andrew E.. Hybrid rocket system and integrated motor for use therein. USP1998025715675.
  7. Jones Herbert Stephen ; Williams Harry Phillip. Hybrid-LO2-LH2 low cost launch vehicle. USP1998065765361.
  8. Kline Korey R. ; Smith Kevin W. ; Bales Thomas O.. Integral solid booster and hybrid thrust sustaining system and projectile incorporating the same. USP2000106125763.
  9. Connell Donald R. ; Cuffe Jeremy P. B.. Liquid oxygen gasifying system for rocket engines. USP1999075918460.
  10. Katorgin Boris Ivanovich,RUX ; Chvanov Vladimir Konstantinovich,RUX ; Derkach Gennady Grigorievich,RUX ; Movchan Jury Vasilievich,RUX ; Chelkis Felix Jurievich,RUX ; Semenov Vadim Iliich,RUX ; Tolsti. Liquid-propellant rocket engine with turbine gas afterburning. USP2001056226980.
  11. Jacobson Michael D. ; Burgner Gary R.. Multi-ignition controllable solid-propellant gas generator. USP2001066250072.
  12. McDonald Allan J. (Pleasant View UT). Multiple propellant solid rocket motor. USP1989064840024.
  13. Kevin W. Smith ; Theodore C. Slack, Jr. ; Korey R. Kline ; Thomas O. Bales, Jr.. Propulsion system containing a mixed-phase propellant and a method for propelling an object with the same. USP2002046367244.
  14. Koppel Christophe,FRX ; Maine Laurent,FRX. Pulse rocket engine. USP1999085941062.
  15. Rosenfield Gary C. (Las Vegas NV). Pyrotechnic valve, igniter and combustion preheater for hybrid rocket motors. USP1996125579636.
  16. Chew William M. (Huntsville AL) Asaoka Leo K. (Huntsville AL) Lilley Jay S. (Huntsville AL) May Douglas L. (Huntsville AL). Solid fuel ducted rocket with gel-oxidizer augmentation propulsion. USP1992105152136.
  17. Keirsey James L. (Silver Spring MD). Solid fuel ramjet flow control device. USP1986124628688.
  18. Jones H. Stephen. Stable-combustion oxidizer for hybrid rockets. USP2000066073437.