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.