启动过程推力器喷注管内推进剂流的温降

Temperature drop of propellant stream in injection-tube of thruster during start process

根据空间发动机的总体结构、环境特点和能量守恒原理,提出推进剂在推力器喷注管内流动降温的简化数理模型,研究启动时单元推进剂在推力器喷注管内的流动降温现象。耦合求解推进剂流和喷注管能量方程,可以获得单元推力器喷注管单推三流整体温度的沿程分布规律。用推进剂模拟液实际考察和验证推力器喷注管的流动特点和理论模型的计算结果,分析推进剂流速、喷注管长度和内径对推进剂流温度变化的影响,导出推进剂流前缘出口温度和这3个物理参量间的拟合关系式。研究结果对推力器的热控设计有参考价值。

The temperature drop of propellant stream in injection-tube of the thruster during start process was studied. The physical and numerical model was put forward to calculate the temperature drop of the propellant（ mono-3 ） while flowing through the injection-tube. The temperature of the propellant stream along the injection-tube was obtained by calculating the coupling energy equations of the propellant and the injection-tube, and the results agreed well with the test data of the thruster injection-tube cryogenic flowing experiment. Three factors that affect the temperature drop of the propellant were analyzed, which are the flow velocity of the propellant, the length and the inner diameter of injection-tube. The relationship among the outlet temperature of the first segment propellant and these factors was educed. The results can be used to judge whether the propellant freeze or not after it was injected into the injection-tube and to provide the reliable criterion for the thermal control design of the attitude-control thruster.