Propulsion theoretical and experimental analysis of composite propellants motors

Document Type : Original Article


1 School of Chemical Engineering, Military Technical College, Cairo, Egypt.

2 School of Chemical Engineering, Military Technical College, Cairo, Egypt., Nanotechnology Research Centre, Military Technical College, Cairo, Egypt.



Rockets have revolutionized space technology and human space exploration. Most rockets and missiles are both propelled by rocket motors that use composite solid propellants. The ICT code and the NSAS CEA code are two programs that can be used to forecast theoretical propulsion parameters for composite solid rocket propellant. Rocket propellant
performance is governed by a specific impulse factor, which is calculated theoretical and experiment. In this paper, the theoretical specific impulse for different composite solid propellant formulations at 70 bar combustion pressure and an adapted nozzle (optimum expansion) were calculated by the NASA-CEA code and the ICT code. Meanwhile, a static
firing test was performed on a small scale test motor to experimentally determine the actual specific impulse. The objective is to verify theoretical calculations from two codes with experimental data, via the determination of the specific impulse deviation co-efficient.


Main Subjects