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| 单组元推力室在真空深冷环境中的降温分析 |
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肖泽娟1,2, 李鹏1,2, 程惠尔1,2, 周红玲3,4, 黄瑞生3,4
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1.上海交通大学航空航天系;2.上海200030;3.上海航天动力机械研究所;4.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。 |
| 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 |
| DOI： |
| 分类号:V434.24 |
| 基金项目: |
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| 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,HUANG Rui-sheng
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1.Dept. of Aeronautics and Astronautics, Shanghai Jiaotong Univ, Shanghai 200030,China;2.Shanghai Spaceflight (Inst of) Power Machinery,Shanghai 200233, China
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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. |
| Key words: Monopropellant rocket engine Thruster chamber Low temperature vacuum test Thermal analysis |
