Merits of full flow vs. conventional staged combustion cycles for reusable launch vehicle propulsion
Merits of full flow vs. conventional staged combustion cycles for reusable launch vehicle propulsion
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可重复使用运载火箭推进的全流式燃烧循环与传统分级燃烧循环的优点
DOI：
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发表时间：
2008
期刊：
影响因子：
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通讯作者：
R. Parsley
中科院分区：
文献类型：
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作者：
S. Peery;R. Parsley
本文比较了用于可重复使用运载火箭、单级到轨的全流量和常规分级燃烧热力学O2/H2火箭发动机循环。给出了循环热力学、部件结构和部件运行参数对两种方案发动机性能和重量的影响。这两个循环都采用了同等技术的叶轮机械和燃烧室/喷嘴RLV寿命要求来模拟。给出了循环选择、泵出口压力和涡轮温度对SSTO可重复使用运载火箭空重的一阶影响。
This paper provides a comparison between full‐flow and conventional staged combustion thermodynamic O2/H2 rocket engine cycles for Reusable Launch Vehicle, RLV, single‐stage‐to‐orbit applications. The impact of the cycle thermodynamics, component configuration, and component operating parameters on engine performance and weight for the two approaches is presented. Both cycles were modeled with equivalent technology turbomachinery and chamber/nozzle RLV life requirements. The first order impact of cycle selection, pump exit pressure, and turbine temperature on the empty weight of an SSTO Reusable Launch Vehicle is presented.