SELECTION AND PERFORMANCE OF HYBRID PROPELLANT PROPULSION SYSTEM | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 7, Volume 10, 10th International Conference On Aerospace Sciences & Aviation Technology, May 2003, Page 89-97 PDF (1.7 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.24411 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| HOSAM E. M1; LUDViK F.2 | ||||
| 1Egyptian Armed Forces, MTC, Cairo-Egypt. | ||||
| 2Professor, Dpt. of Rocketry, Military Academy in Bmo, Czech Republic. | ||||
| Abstract | ||||
| Hybrid propulsion systems have many advantages when compared to the conventional solid or liquid propellant propulsion systems. Trials leading to eliminate the LP disadvantages, based on theoretical as well as experimental research, lead to broader HPRM applications. In order to select the suitable propellant, it is better to investigate at first such combination of propellant components that have high initial density and secures chemical reactions with the highest reactivity. This paper discusses some typical choices for fuel and oxidizer and advantages and disadvantages of each one. Comparing the magnitude of specific impulse, various fuel-oxidizer combinations and mass-mixing ratio, burning law exponent and optimum design of the solid fuel grain, help to obtain better HP advantages. Moreover, it is not beyond possibility that further dedicated research and development of the hybrid propellants will relieve some of the inefficiency problems and therefore boost the performance figures even higher. It is anticipated that hybrids could dominate the chemical propulsion field in that century. | ||||
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