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

xxl\Debug\DF60.PDB
...\.....\xxl.exe
...\.....\xxl.pdb
...\shuchu1.dat
...\shuru1.dat
...\the establish of Pc.lpk
...\xxl.dsp
...\xxl.dsw
...\xxl.f90
...\xxl.opt
...\xxl.plg
...\Debug
xxl

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