Commenced in January 2007
Frequency: Monthly
Edition: International
Paper Count: 32451
Hybrid Rocket Motor Performance Parameters: Theoretical and Experimental Evaluation

Authors: A. El-S. Makled, M. K. Al-Tamimi


A mathematical model to predict the performance parameters (thrusts, chamber pressures, fuel mass flow rates, mixture ratios, and regression rates during firing time) of hybrid rocket motor (HRM) is evaluated. The internal ballistic (IB) hybrid combustion model assumes that the solid fuel surface regression rate is controlled only by heat transfer (convective and radiative) from flame zone to solid fuel burning surface. A laboratory HRM is designed, manufactured, and tested for low thrust profile space missions (10-15 N) and for validating the mathematical model (computer program). The polymer material and gaseous oxidizer which are selected for this experimental work are polymethyle-methacrylate (PMMA) and polyethylene (PE) as solid fuel grain and gaseous oxygen (GO2) as oxidizer. The variation of various operational parameters with time is determined systematically and experimentally in firing of up to 20 seconds, and an average combustion efficiency of 95% of theory is achieved, which was the goal of these experiments. The comparison between recording fire data and predicting analytical parameters shows good agreement with the error that does not exceed 4.5% during all firing time. The current mathematical (computer) code can be used as a powerful tool for HRM analytical design parameters.

Keywords: Hybrid combustion, internal ballistics, hybrid rocket motor, performance parameters.

Digital Object Identifier (DOI):

Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 1672


[1] Migireanu F. “Small Launcher Enabled by Hybrid Rocket Motor Technology” 17th Int. Conference on Applied Mechanics Eng., April 19-21, MTC, Cairo, 2016
[2] Masahiro K., Fumio K. and Toru S. “Design Optimization Of Launch Vehicle Concept Using Cluster Hybrid Rocket Engine for Future Space Transportation” journal of fluid science and technology, vol. 11, No. 1, Paper No.15-00151, 2016
[3] Humble, R., Henry Gary N., Larson Wiley J., “Propulsion System Analysis and Design”, United States Air Force Academy, 1995.
[4] Sutton G.: “Rocket Propulsion Elements”, Sixth Edition, John Wiley, New York, 1992.
[5] Barrere M. et al., “Rocket Propulsion”, Elsevier Publishing Company, 1960.
[6] Marxman C. A., Wooldridge C. E. and Muzzy R. J.: Fundamentals of hybrid boundary layer combustion, Heterogeneous combustion, progress in Astronauts and aeronautics, vol. 15, Academic press, New York, 1964.
[7] Wooldridge C. E. and Muzzy R. J. “Internal Ballistic Considerations in Hybrid Rocket Design”, J. Spacecraft, Vol. 4, No. 2, Feb. 1967.
[8] David W. Netzer “Hybrid Rocket Internal Ballistics”, Naval Postgraduate School, Monterey, January 1972.
[9] A. EL-S. Makled “Prediction of Hybrid Combustion Boundary Layer Parameters” 12th International Conference on Aerospace Sciences & Aviation Technology (ASAT-12), BAL-02, MTC, Cairo, May 29 – 31, 2007.
[10] Curt Selph “Computer Program for Calculation of Complex Chemical Equilibrium Composition”, NASA SP-273, United States Air Force Academy, version, July 1994.