端面燃烧固体火箭发动机压强建立过程计算程序 输入为比热比，燃气气体常数，点火温度，推进剂密度，装药直径，喷管喉部直径，装药体积，燃速相关常数 输出为压强和工作时间-Face charge calculation of solid rocket motor process of establishing the working pressure

Input for the specific heat ratio, gas gas constant, ignition temperature, propellant density, charge diameter, nozzle throat diameter, charge volume, related to burning rate constant, the ignition pressure output and working hours for the pressure