Two-component propellant grain for rocket motor: Combustion analysis and geometric optimization

The paper considers utilization of rocket motor propellant grains that consist two propellants. idea is to achieve approximately neutral burning using an outer surface inhibited cylindrical shape and complex contact between An existing grain with geometry has been analytically modeled in terms determination evolution corresponding areas. analytical experimental results? diagrams this have found a saw-tooth because the segments separate propellants, causing potential problems process during relatively short active phase, showing obvious need for further optimization. This created opportunity development improved mathematical model main interior ballistic parameters. Comparison calculation results based on both models experimentally determined chamber pressure data shows very good agreement. Therefore, two-component significant application possibilities suggested modeling approaches.