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특허 상세정보

Hybrid helium heater pressurization system and electrical ignition system for pressure-fed hybrid rockets

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-009/72    F02K-009/50   
미국특허분류(USC) 60/259 ; 60/039.48 ; 60/726 ; 60/251
출원번호 US-0322781 (1994-10-13)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Pravel, Hewitt, Kimball & Krieger
인용정보 피인용 횟수 : 12  인용 특허 : 0
초록

A system for pressurizing a liquid oxygen tank (20) in a pressure-fed hybrid rocket (100) provides pressure at a first end of the tank (20) so that liquid oxygen can exit the second end. A hybrid heater (50) creates the pressure by mixing gaseous oxygen with the solid fuel (51) in the hybrid heater (50) to create an extremely high temperature. Helium is then mixed with the combustion products via an inlet (60) and this hot, inert mixture enters the liquid oxygen tank (20) via a diffuser (70). A second hybrid heater (90) pressurizes the gaseous helium sph...

대표
청구항

[ I claim:] [1.] Apparatus including a hybrid heater pressurization system, for a rocket comprising a first liquid fuel component and a second fuel component, comprising pressurization means, for forcing the first liquid fuel component into contact with the second fuel component, the pressurization means comprising:(I) a gas initially stored at a cryogenic temperature;(ii) a hybrid heater having a longitudinal axis and generating combustion products when ignited for heating the gas by mixing the combustion products of the hybrid heater with the gas in a ...

이 특허를 인용한 특허 피인용횟수: 12

  1. Beck, Philip; Kutter, Bernard; Zegler, Frank. Airborne gas storage and supply system. USP2003126658863.
  2. Kline, Korey R.; Smith, Kevin W.; Cesaroni, Anthony Joseph. Flame holder for a hybrid rocket motor. USP2004056739121.
  3. Kline, Korey R.; Smith, Kevin W.. Hybrid rocket motor having a precombustion chamber. USP2004016679049.
  4. Kline, Korey R.; Smith, Kevin W.. Hybrid rocket motor having a precombustion chamber. USP2004116820412.
  5. Kline, Korey R.; Smith, Kevin W.; Bales, Thomas O.. Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent. USP2004026684625.
  6. Kline, Korey R.; Smith, Kevin W.; Schmidt, Eric E.; Bales, Thomas O.. Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent. USP2003116640536.
  7. Smith Kevin W. ; Kline Korey R. ; Slack ; Jr. Theodore C. ; Mossberg Andrew E.. Hybrid rocket system and integrated motor for use therein. USP1999045893266.
  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. Hayoun, David; Danguy, Francois; Sannino, Jean Michel; Noir, Pascal Marcel Jean. Pressurizing device and method. USP2016059341315.
  10. 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.
  11. Bahn, Patrick R. E.. Rocket engine systems. USP2017069677503.
  12. Jones H. Stephen. Stable-combustion oxidizer for hybrid rockets. USP2000066073437.