论文部分内容阅读
固体火箭发动机喷管喉部的沉积物对内弹道性能影响很大.发生沉积时,沉积物的沉积速率与燃气传给冷壁面的热量及喉部壁面的温度梯度等因素密切相关.本文通过对喉部移动边界传热问题的分析提出沉积物的沉积变化规律为:在沉积物表面温度达到熔点之前,沉积速率为常数;而在达到熔点之后,则按指数规律衰减,并提供了相应的计算公式. 最后将理论计算与发生沉积的二例发动机试车曲线进行了比较.结果证明,理论结果与实际试车结果十分吻合,这样为控制与消除沉积现象提供了理论依据.
Sediment of throat of solid rocket motor launcher has a great influence on the internal ballistic performance.The deposition rate of sediment is closely related to the heat transfer from gas to cold wall and the temperature gradient of throat wall, The analysis of the heat transfer problem at the moving boundary of the throat suggests that the deposition variation law of the sediment is that the sedimentation rate is constant before the surface temperature of the sediment reaches the melting point and decays exponentially after the melting point is reached and provides the corresponding calculation Formula.At the end of this paper, the theoretical calculation and the deposition curves of two engine test curves are compared.The results show that the theoretical results are in good agreement with the actual test results, which provides a theoretical basis for controlling and eliminating the sedimentation phenomenon.