Abstract
Evidence suggests that rocket assisted projectiles (RAP) is among the most important factors to extend the range of the large caliber ammunition over standard gun systems. To date, there are few studies that have investigated the association between the mechanical properties of solid rocket propellant and the high acceleration forces which experienced by the rocket assisted projectiles (RAP) when it is launched. In the present paper, the effects of binder percentages and the stoichiometric ratio of isocyanate and hydroxyl groups (NCO/OH ratio) were used for investigating the mechanical and ballistic performance of composite solid rocket propellants (CSRP). Theoretical thermodynamic combustion properties of propellants formulations of the base binder hydroxyl terminated polybutadiene with solid loading above 60% have been calculated using the ICT-Thermodynamic Code v7.00, in order to assess the theoretical energetic performances of composite propellants as a function of their compositions.