| 单组元推力室在真空深冷环境中的降温分析 |
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| 引用本文： | 肖泽娟,李鹏,程惠尔,周红玲,黄瑞生.单组元推力室在真空深冷环境中的降温分析[J].推进技术,2005,26(2):116-119. |
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| 作者姓名： | 肖泽娟 李鹏 程惠尔 周红玲 黄瑞生 |
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| 作者单位： | 1. 上海交通大学,航空航天系,上海,200030
2. 上海航天动力机械研究所,上海,200233 |
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| 摘 要： | 基于能量守恒原理，提出单组元推力室毛细喷注管和集合器、喷注板、支架等主要部件在真空深冷环境中耦合传热的物理模型和数学方程，并据此求得一台10N单组元发动机的典型降温规律。计算结果与发动机地面真空低温模拟试验数据作了比对，两者较为一致。喷注管壁温是推进剂流动降温计算的热边界条件和喷注管内推进剂会不会结冰的判据。
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| 关 键 词： | 单元推进剂火箭发动机 推力室 低温真空试验 热分析 |
| 文章编号： | 1001-4055(2005)02-0116-04 |
| 修稿时间： | 2004年5月16日 |
Temperature drop analysis on the monopropellant thruster in the vacuum cryogenic environment |
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| XIAO Ze-juan,I Peng,CHENG Hui-er,ZHOU Hong-ling and HUANG Rui-sheng.Temperature drop analysis on the monopropellant thruster in the vacuum cryogenic environment[J].Journal of Propulsion Technology,2005,26(2):116-119. |
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| Authors: | XIAO Ze-juan I Peng CHENG Hui-er ZHOU Hong-ling and HUANG Rui-sheng |
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| Institution: | XIAO Ze-juan~1,LI Peng~1,CHENG Hui-er~1,ZHOU Hong-ling~2,HUANG Rui-sheng~2 |
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| Abstract: | Based on the conversation of energy principle, the coupling heat-transfer physical model and a set of mathematical equations were put forward to calculate the capillary spray-tube, the aggregate-organ, the spray-plate and the bracket etc., the main components of the thruster, as they exposing to the vacuum cryogenic environment,and a typical temperature drop process about a 10N monopropellant engine were calculated by this computational model.The calculation results agree well with the test data by vacuum cryogenic simulation experiment performed on the ground.The temperature of the spray-tube is the thermal boundary conditions for the propellant temperature drop calculation while flowing through the spray-tube and it has provided the criterion to judge whether the propellant freeze or not. |
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| Keywords: | Monopropellant rocket engine Thruster chamber Low temperature vacuum test Thermal analysis |
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