| 小推力高室压NTO/MMH火箭发动机实验系统管路流阻特性实验 |
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| 引用本文： | 刘洌,卫强,方忠坚,梁国柱,张学军. 小推力高室压NTO/MMH火箭发动机实验系统管路流阻特性实验[J]. 航空动力学报, 2016, 31(3): 746-755. DOI: 10.13224/j.cnki.jasp.2016.03.028 |
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| 作者姓名： | 刘洌 卫强 方忠坚 梁国柱 张学军 |
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| 作者单位： | 1. 北京航空航天大学 宇航学院, 北京 100191; |
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| 摘 要： | 为研究小推力高室压NTO/MMH(四氧化二氮/甲基肼)火箭发动机实验系统管路流阻特性,对管路流阻理论、冷流实验及点火实验进行对比分析研究.通过管路介质流动能量损失计算,建立NTO/MMH管路流阻特性理论模型.开展无水乙醇冷流实验及NTO/MMH小推力高室压火箭发动机点火实验,以最小二乘法确定流阻特性实验拟合公式.与冷流实验结果相比,无水乙醇流量分别为0.10~0.40kg/s,0.09~0.36kg/s时,NTO/MMH管路理论流阻平均误差分别为5.42%,3.67%;与点火实验结果相比,真实推进剂流量分别为0.39~0.47kg/s,0.26~0.31kg/s时,NTO/MMH管路理论流阻平均误差分别为2.44%,2.47%,基于冷流实验预测的流阻平均误差分别为5.74%,3.46%,NTO流量为0.47~0.51kg/s(不含0.47kg/s)时,管路理论与冷流实验预测的流阻平均误差分别为16.56%,9.73%.实验与分析结果可应用于小推力高室压NTO/MMH发动机点火实验,并为实验系统设计提供必要支持.
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| 关 键 词： | 小推力液体火箭发动机 高压实验系统 流阻特性 冷流实验 点火实验 |
| 收稿时间： | 2014-07-23 |
Pipe flow resistance characteristics of test system for low-thrust NTO/MMH rocket engines with high chamber pressure |
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| LIU Lie,WEI Qiang,FANG Zhong-jian,LIANG Guo-zhu and ZHANG Xue-jun. Pipe flow resistance characteristics of test system for low-thrust NTO/MMH rocket engines with high chamber pressure[J]. Journal of Aerospace Power, 2016, 31(3): 746-755. DOI: 10.13224/j.cnki.jasp.2016.03.028 |
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| Authors: | LIU Lie WEI Qiang FANG Zhong-jian LIANG Guo-zhu ZHANG Xue-jun |
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| Affiliation: | 1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;2. Beijing Institute of Aerospace Testing Technology, Academy of Aerospace Propulsion Technology, China Aerospace Science and Technology Corporation, Beijing 100074, China |
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| Abstract: | To research the pipe flow resistance characteristics of the low-thrust NTO/MMH(nitrogen tetroxide/methyl hydrazine) rocket engine with high chamber pressure, comparative analysis of pipe flow resistances on the theoretical analysis, cold-flow tests and firing tests were conducted. According to the calculation methods of flow energy loss, the theoretical analysis models of NTO/MMH pipe flow resistance were established. After alcohol-cold-flow tests and low-thrust NTO/MMH rocket engine's firing tests with high chamber pressure, the pipe flow resistance characteristics fitting formulas based on test results were obtained with the least-square method. Compared with the cold-flow test results, when mass flow rates of alcohol were 0.10~0.40kg/s, 0.09~0.36kg/s respectively, the average errors of theoretical flow resistances of NTO/MMH pipes were 5.42% and 3.67%. With the results of firing tests, when mass flow rates of NTO/MMH were 0.39~0.47kg/s, 0.26~0.31kg/s respectively, the average errors of theoretical flow resistances of NTO/MMH pipes were 2.44% and 2.47%, and those based on cold-flow tests of NTO/MMH pipes were 5.74% and 3.46%, but when mass flow rates of NTO were 0.47~0.51kg/s(without 0.47kg/s), the average errors of theoretical flow resistence and cold-flow tests increased to 16.56% and 9.73%. These NTO/MMH flow resistance characteristics acquired from firing tests could be applied in the firing test, providing a necessary support in design of the rocket engine test system in the future. |
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| Keywords: | low-thrust liquid rocket engine high pressure test system flow resistance characteristics cold-flow test firing test |
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