小推力液体火箭发动机在轨热分析  

Thermal analysis of low-thrust liquid rocket engine on orbit

作　　者：闫波 张会强[1] 王兵[1] YAN Bo;ZHANG Huiqiang;WANG Bing(School of Aerospace,Tsinghua University,Beijing 100084,China;Research and Development Center,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]清华大学航天航空学院,北京100084 [2]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《火箭推进》2019年第3期15-19,69,共6页Journal of Rocket Propulsion

摘　　要：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10K;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71.41K,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.

关 键 词：液体火箭发动机 小推力 太阳辐射 数值仿真 热分析 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程] TB131[理学—物理]