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	RBCC的可实现性方案-DRBCC分析
	张倩 ; 王兵 ; 张耘隆 ; 张会强 ; ZHANG Qian ; WANG Bing ; ZHANG Yun-long ; ZHANG Hui-qiang
	2016-03-30 ; 2016-03-30
关键词	火箭基组合动力 引射火箭 超燃冲压发动机 液氧/甲烷火箭发动机 graduate education category structure match demand and supply of human resources V434
其他题名	An analysis of RBCC realizability scheme:DRBCC
中文摘要	提出了液氧/空气/甲烷DRBCC(dual rocket-based combined cycle)推进系统。在该系统中,引射火箭和纯火箭采用液氧/甲烷补燃循环系统。在引射火箭模态,液氧/甲烷富燃预燃过程工作,其富燃燃气作为引射源吸入和加热空气,并与空气补燃。在超燃冲压模态,液氧/甲烷富燃预燃过程产生的燃气可以增强超燃过程或作为超燃模态的燃料,降低超燃模态的技术难度。在纯火箭模态,液氧/甲烷闭式补燃循环系统处于全过程工作状态。因此,在DRBCC推进系统中,引射火箭、超燃模态和纯火箭模态高度融合和兼顾,并采用单一燃料,使液氧/空气/甲烷DRBCC推进系统具有良好的可实现性。; A dual rocket-based combined cycle(DRBCC) propulsion system with LOX/air/methane as propellants is proposed in this paper.In this system,the LOX/methane staged combustion cycle system is adopted for both the ejecctor and pure rocket modes.For the rocket-ejector and scramjet modes,the LOX/methane staged cycle runs at the half working-condition,where only the fuel-rich LOX/methane pre-combustion process works.In the rocket-ejector mode,the fuel-rich burned hot gas functions as the ejecting source,and thus reburns with air.In the scramjet mode,such fuel-rich hot gas can be used to enhance the supersonic combustion or as fuel,which is helpful to reduce the technical difficulty of scramjet mode.In the pure rocket mode,the closed-cycle system of Lox/methane staged combustion rocket cycle works at full load state.The ejector-rocket,scramjet and pure rocket modes in DRBCC are therefore highly integrated based on the half-load or full-load state of the LOX/methane staged rocket cycle,and single fuel of methane is adopted in whole process of DRBCC.Such advantages are benefit to archive a well realized RBCC system.
语种	中文 ; 中文
内容类型	期刊论文
源URL	[http://ir.lib.tsinghua.edu.cn/ir/item.do?handle=123456789/143725]
专题	清华大学
推荐引用方式 GB/T 7714	张倩,王兵,张耘隆,等. RBCC的可实现性方案-DRBCC分析[J],2016, 2016.
APA	张倩.,王兵.,张耘隆.,张会强.,ZHANG Qian.,...&ZHANG Hui-qiang.(2016).RBCC的可实现性方案-DRBCC分析..
MLA	张倩,et al."RBCC的可实现性方案-DRBCC分析".(2016).

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