Propulsion theoretical and experimental analysis of composite propellants motors | ||
| International Conference on Aerospace Sciences and Aviation Technology | ||
| Volume 20, Issue 20, May 2023, Pages 1-8 PDF (1.17 M) | ||
| Document Type: Original Article | ||
| DOI: 10.1088/1742-6596/2616/1/012057 | ||
| Authors | ||
| A Said* 1; A Maraden1; T M Elhedery1; A M abd Elall1; S Elbasuney2 | ||
| 1School of Chemical Engineering, Military Technical College, Cairo, Egypt. | ||
| 2School of Chemical Engineering, Military Technical College, Cairo, Egypt., Nanotechnology Research Centre, Military Technical College, Cairo, Egypt. | ||
| Abstract | ||
| 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. | ||
| Keywords | ||
| Composite solid propellant; NASA CEA; ICT Code; and Specific impulse | ||
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