Book Description
A digital computer analog model of a solid propellant rocket motor and performance evaluation system was developed. Heat and mass balance effects of the igniter, propellant, and insulation during ignition and chamber filling were modeled. Results include investigation of flame spreading, ignition criteria, and contribution by insulation to motor performance. Comparisons of predictions and experimental tests are included. An IBM model 7094 computer was used for the analysis. The FORTRAN computer program is included. (Author).