火箭推进

为了获得太阳辐射对深空探测小推力液体火箭发动机结构热特性的影响,对在轨运行液体火箭发动机推力室热环境进行了分析。考虑太阳辐射对模型非均匀性的影响,根据发动机的实体模型,在ANSYS Workbench 环境下引入APDL 语言,建立其三维稳态热分析有限元模型。针对在地球同步轨道(GEO)的空间小推力发动机实际工作情况,分别对发动机推力室稳态工作和发动机不工作状态进行结构热情况分析研究,得出太阳辐射对发动机温度分布的影响规律。稳态工作时太阳辐射对推力室温度影响不大,有太阳辐射和没太阳辐射推力室室壁温度最大差值10 K; 发动机不工作时发动机接受太阳辐射面温度较高,有太阳辐射和没太阳辐射推力室室壁温度最大差值71.41 K,太阳辐射对模型的非均匀性影响较大。该研究结果可为小推力发动机的热设计提供依据。

In order to obtain the influence of solar radiation on the thermal characteristics of low-thrust liquid rocket engine for deep-space-exploration, this paper analyzes the thermal environment of thrust chamber for the liquid rocket engine on orbit.Solar radiation is considered due to its effect on the heterogeneity of temperature field.With considering the structure of a liquid rocket engine, APDL is introduced into ANSYS Workbench to build a finite element model for simulating its three-dimensional steady-state thermal analysis.In view of the actual working situation of low-thrust liquid engine in geosynchronous orbit(GEO), the structural temperature changes of the engine thrust chamber during steady working and not working are analyzed, respectively.The influence of solar radiation on the temperature field is obtained.The solar radiation has little effect on the thrust chamber temperature during the steady state operation.The maximum difference of chamber wall temperature between solar radiation and non-solar radiation is 10 K.When the engine is not working, the engine surface temperature with receiving solar radiation is higher, and the maximum temperature difference is 71.41 K.The solar radiation has a great influence on the non-uniformity of the model.This research provides a criterion to the thermal design of low-thrust liquid rocket engine.

引言
1 GEO轨道外热流计算方法
2 有限元数值仿真模型
3 数值仿真结果分析
4 结论

图1 太阳辐射热流图<br/>Fig.1 Heat flow diagram of solar radiation

图1 太阳辐射热流图
Fig.1 Heat flow diagram of solar radiation

表1 发动机综合参数<br/>Tab.1 Integrated parameters of engine

表1 发动机综合参数
Tab.1 Integrated parameters of engine

图2 燃气(液膜)沿轴向温度分布<br/>Fig.2 Distribution of gas(liquid film)temperature along the axial

图2 燃气(液膜)沿轴向温度分布
Fig.2 Distribution of gas(liquid film)temperature along the axial

图3 燃气(液膜)沿壁面对流换热系数分布<br/>Fig.3 Distribution of gas(liquid film)convection heat transfer coefficient along the wall

图3 燃气(液膜)沿壁面对流换热系数分布
Fig.3 Distribution of gas(liquid film)convection heat transfer coefficient along the wall

图4 太阳辐射方向<br/>Fig.4 Direction of solar radiation

图4 太阳辐射方向
Fig.4 Direction of solar radiation

表2 喷注器管道对流换热系数<br/>Tab.2 Convective heat transfer coefficient of injector pipe

表2 喷注器管道对流换热系数
Tab.2 Convective heat transfer coefficient of injector pipe

图5 有太阳辐射稳态工作推力室壁温分布<br/>Fig.5 Wall temperature distribution of thrust chamber with solar radiation in steady working

图5 有太阳辐射稳态工作推力室壁温分布
Fig.5 Wall temperature distribution of thrust chamber with solar radiation in steady working

图6 无太阳辐射稳态工作推力室壁温分布<br/>Fig.6 Wall temperature distribution of thrust chamberwithout solar radiation in steady working

图6 无太阳辐射稳态工作推力室壁温分布
Fig.6 Wall temperature distribution of thrust chamberwithout solar radiation in steady working

图7 有太阳辐射发动机不工作时推力室壁温分布<br/>Fig.7 Wall temperature distribution of thrust chamber with solar radiation under not working condition

图7 有太阳辐射发动机不工作时推力室壁温分布
Fig.7 Wall temperature distribution of thrust chamber with solar radiation under not working condition

图8 推力室壁温沿轴向变化曲线<br/>Fig.8 Changing curve of thrust chamber wall temperature along the axial

图8 推力室壁温沿轴向变化曲线
Fig.8 Changing curve of thrust chamber wall temperature along the axial

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备注

引言

1 GEO轨道外热流计算方法

2 有限元数值仿真模型

3 数值仿真结果分析

4 结论

期刊信息