点火管流量的确定

本文就固体火箭发动机中采用的点火管提出了一维两相流动模型,并用差分方法求解模型方程,得点火管流量。为了验证计算结果进行了实验。计算和实验结果对比表明趋势一致。本文还给出了药粒粒径和药量对点火管内压力的影响。

DETERMINATION OF MASS FLUX FOR IGNITRON

An one-dimensional two-phase flow model is put forward for ignitron in solid propellant rocket,and its governing equations are derived. The gas pressure,tempera-ture,density and particle velocity in the ignitron are obtained from solution of the equations by finite difference method. A experimental apparatus has been set up to testify the calculations. From analyzing the results of the calculations and experiments the following conclusions are drawn. First, consistency of the flux calculated with the flux measured proves feasibility of the present calculation method;Second, the particle size and charge of igniter have significant effects on pressure in the ignitron; Third, the gas pressure,temperature and density in the burned area change very little, but the gas and particle velocities vary a lot; Last, the acceleration of flame spreading which comes from the calculations is testified in the experiments.