Solid rocket motors internal ballistic model with erosive and condensed phase considerations

Abstract

An interior ballistics model was implemented and applied for a double base and composite propellant boosters to be used for a boosted dart suborbital vehicle. Erosion and condensed phase are taken into account and numerical results are shown in comparison with experimental data obtained on test firings for each motor. Fast calculation of the main parameters of the solid rocket motor unit (thrust, burn time, specific impulse, total impulse) is available. The solid fuel characteristics and motor geometry are contained within two input files while the results of the calculations are presented to the user in a several output files.