摘要
本文用有限元方法对液氢液氧火箭发动机的氢泵起动前预冷进行了瞬态温度场计算。通过理论计算与试验结果比较,表明模型的建立、计算方法及程序是基本可靠的,缩短预冷时间是可行的。本文计算方法简单,程序通用性强,它为数值模拟部分替代实物模型试验做了初步尝试并取得了一些经验,可以做为地面试验的辅相工具。
In this paper, the finite element method is used to calculate transient temperature field distribution of hydrogen pump chilldown in liquid rocket engine before the engine starts. Chilldown flux and cnilldown time are related to consuming of liquid hj'drogen. If chilldown flux or time is not enough, it may produce bad effect on engine start's reliability. If excessive liquid hydrogen were consumed, payload would be diminished. Therefore, eifectively reducing chilldown time has important engineering value. In order to simplify the complicated structure of hydrogen pump, this paper establishes a two-dimension axial symmetry mathematical model, the results obtained by this model fit well with the experimental data, it is confirmed that the mathematical and physical model are correct, and calculation method and computer program are reliable. It is possible to diminish chilldown time in present engineering condition. The numerical calculation analyses transient temperature changing regular pattern of inner wall of hydrogen pump. This result plays an active part in researching chilldown time. In addiation, this paper achieves a good experience by numerical calculation partially replacing material model experiment It will serve the ground experiment much better.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1992年第2期79-86,共8页
Journal of Astronautics
