| 液氧/丙烷推力室试验研究 |
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| 引用本文： | 张中光,郑秀琴.液氧/丙烷推力室试验研究[J].推进技术,1992,13(1):50-56. |
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| 作者姓名： | 张中光 郑秀琴 |
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| 作者单位： | 上海航天局801所
(张中光)，上海航天局801所(郑秀琴) |
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| 摘 要： | 1987～1989年间进行的液氧/丙烷推力室试验研究内容主要涉及点火和启动、燃烧、传热等。目的在于探索液氧/丙烷推进剂的技术关键,为新型液氧/烃发动机论证提供必要依据。使用了两种结构状态的推力室。试验室压2.5～7.8MPa。推力8～25kN(真空)。通过试验,考核了液氧/丙烷推进剂的点火和燃烧性能,验证了丙烷再生冷却的可行性;并与四氧化二氮/偏二甲肼自燃推进剂、液氧/煤油推进剂的试验情况进行了比较。
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| 关 键 词： | 液氧 丙烷 推力室 试验 火箭发动机 |
EXPERIMENTAL INVESTIGATION ON LOX/PROPANE THRUST CHAMBER |
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| Zhang Zhongguang and Zheng Xiuqin.EXPERIMENTAL INVESTIGATION ON LOX/PROPANE THRUST CHAMBER[J].Journal of Propulsion Technology,1992,13(1):50-56. |
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| Authors: | Zhang Zhongguang and Zheng Xiuqin |
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| Institution: | The 801st Research Institute |
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| Abstract: | An experimantal investigation on LOX/propane thrust chamber was carried out during 1987-1989.The test mainly involves ignition, start-up, combustion,heat transfer and so on.
The purpose of this test is to explore the key technology of LOX/propane propella-nt and to give the necessary evidence for the demonstration of the advanced LOX/hyd rocarbon engine. In this test, two kinds of the thrust chamber were used, the chamber pressure was from 2.5MPa to 7.8MPa and the range of thrust was 8-25KN (vacuum), with the comparison with the test of N2O4/UDMH hypergolic propellant and LOX/ker-osene propellant, the performance of the ignition and combustion of LOX/propane pr-opellant was verified and the feasibility of propane's regenerative cooling was proved |
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| Keywords: | Liquid oxjrgen Propane Thrust chamber Test |
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