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

刘洌; 卫强; 方忠坚; 梁国柱; 张学军

doi:10.13224/j.cnki.jasp.2016.03.028

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

doi: 10.13224/j.cnki.jasp.2016.03.028

1. 北京航空航天大学宇航学院, 北京 100191;
2. 中国航天科技集团公司航天推进技术研究院北京航天试验技术研究所, 北京 100074

详细信息

作者简介:
刘洌(1988-),男,重庆合川人,博士生,主要从事姿轨控发动机设计、仿真与实验研究.

中图分类号: V434.3
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出版历程
- 收稿日期: 2014-07-23
- 刊出日期: 2016-03-28

Pipe flow resistance characteristics of test system for low-thrust NTO/MMH rocket engines with high chamber pressure

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

摘要

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.
- 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
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.
- low-thrust liquid rocket engine /
- high pressure test system /
- flow resistance characteristics /
- cold-flow test /
- firing test

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