Tactical and technical demands of modern types of composite solid rocket propellant (CSRP) focused recently on decreasing both the primary smoke concentration, by minimizing the amount of solid particle as metal oxides and carbon soot, and secondary smoke concentration, by minimizing the amount of gaseous hydrogen chloride in the exhaust plume. In this work, reports the theoretical and practical methods for determining the primary smoke of composite solid propellant based on energetic material as (AP-HMX-RDX-NaNO3…) and polyurethane (PU) binder based on Hydroxyl terminated polybutadiene (HTPB) which used in many kinds of composite propellant such as Conventional, Scavenger, and non-chlorine and neutralized composite propellant. Formulations were prepared and the densities of primary smoke were experimentally determined. A smoke device was invented for practical measuring of the primary smoke concentration by determining the smoke density and compared with the theoretical results from ICT thermodynamic program which used to calculate the ballistic parameters and smoke concentration of composite propellants. Secondary smoke was experimentally determined then compared with the theoretical data from ICT thermodynamic program which used to calculate the ballistic parameters and smoke concentration of composite propellants.
conventional, scavenger, non-chlorine and neutralized propellant, smoke density