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以液膜冷却结合辐射冷却的液体姿控火箭发动机为研究对象.采用一体化计算模型分析传热,同时应用有限元方法对给定温度条件的热结构进行了耦合分析,最后讨论了推力室在外压作用及温度载荷条件下结构的屈曲稳定性.计算结果与参考的试验结果接近,最高温度误差为3.67%,说明该一体化计算传热模型的有效性.考虑热载荷作用得到的屈曲载荷值较不考虑热载荷作用提高了大约5.793 3%.该结果为工程设计提供了有益的参考.
A liquid film cooling combined with radiatively cooled liquid attitude control rocket motor was taken as the research object.An integrated calculation model was used to analyze the heat transfer and the finite element method was used to analyze the thermal structure of a given temperature condition.Finally, The buckling stability of the structure under the action of pressure and temperature is similar to that of the reference test, the maximum temperature error is 3.67%, which shows the validity of the integrated heat transfer model.Considering the buckling load value The effect of thermal load is less about 5.793 3%, which provides a useful reference for engineering design.