Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-009/72
출원번호
US-0054080
(2002-01-22)
발명자
/ 주소
Kline, Korey R.
Smith, Kevin W.
Bales, Thomas O.
출원인 / 주소
Hy Pat Corporation
대리인 / 주소
Gordon & Jacobson, P.C.
인용정보
피인용 횟수 :
26인용 특허 :
8
초록▼
A hybrid rocket motor includes a storage tank which stores an oxidizer under relatively low pressure, a turbopump preferably directly coupled to an outlet of the storage tank which pressurizes the oxidizer to a relatively high pressure, a combustion chamber including a solid fuel, and an injector be
A hybrid rocket motor includes a storage tank which stores an oxidizer under relatively low pressure, a turbopump preferably directly coupled to an outlet of the storage tank which pressurizes the oxidizer to a relatively high pressure, a combustion chamber including a solid fuel, and an injector between the turbopump and combustion chamber through which the oxidizer is injected into the combustion chamber. According to a preferred aspect of the invention, the turbopump is operated by an expander cycle of a heat exchanger. According to another preferred aspect of the invention, the fluid flowing through the heat exchanger is oxidizer tapped from the storage tank. A barrier is maintained between an oxidizer feed line from the turbopump and the injector until sufficient pressure is created by the turbopump to pump the oxidizer at the requisite pressure into the injector.
대표청구항▼
A hybrid rocket motor includes a storage tank which stores an oxidizer under relatively low pressure, a turbopump preferably directly coupled to an outlet of the storage tank which pressurizes the oxidizer to a relatively high pressure, a combustion chamber including a solid fuel, and an injector be
A hybrid rocket motor includes a storage tank which stores an oxidizer under relatively low pressure, a turbopump preferably directly coupled to an outlet of the storage tank which pressurizes the oxidizer to a relatively high pressure, a combustion chamber including a solid fuel, and an injector between the turbopump and combustion chamber through which the oxidizer is injected into the combustion chamber. According to a preferred aspect of the invention, the turbopump is operated by an expander cycle of a heat exchanger. According to another preferred aspect of the invention, the fluid flowing through the heat exchanger is oxidizer tapped from the storage tank. A barrier is maintained between an oxidizer feed line from the turbopump and the injector until sufficient pressure is created by the turbopump to pump the oxidizer at the requisite pressure into the injector. 9911100, DeLong et al.; US-5065559, 19911100, Zegel et al.; US-5117599, 19920600, Voss; US-5177917, 19930100, del Castillo Von Haucke; US-5209035, 19930500, Hodges et al.; US-5214889, 19930600, Nienhuis et al.; US-5214890, 19930600, Levitan et al.; US-5341615, 19940800, Hodges et al.; US-5394658, 19950300, Schreiner et al.
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이 특허에 인용된 특허 (8)
Wagner William R. (Los Angeles CA), Expander-cycle, turbine-drive, regenerative rocket engine.
Held, Timothy J.; Hostler, Stephen; Miller, Jason D.; Vermeersch, Michael; Xie, Tao, Heat engine and heat to electricity systems and methods with working fluid mass management control.
Held, Timothy James; Hostler, Stephen; Miller, Jason D.; Vermeersch, Michael; Xie, Tao, Heat engine and heat to electricity systems and methods with working fluid mass management control.
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