EXPERIMENTAL EVALUATION ON THE EFFECTS OF ENERGETIC ADDITIVES IN THE HYBRID ROCKET FUEL
DOI:
https://doi.org/10.11113/jtse.v11.219Keywords:
Hybrid Rocket Motors; energetic additives; regression rate; hybrid rocket fuelAbstract
This paper evaluates the viability of employing paraffin wax including energetic additives as solid fuel in a hybrid rocket. In this paper, three distinct fuel compositions were used to compare the augmentation of the regression rate. Hybrid rockets combine the best characteristics of solid and liquid rockets, and they provide a multitude of advantages, such as safe handling and storage, a wider variety of fuel, a lower price, and enhanced dependability. However, it has a key drawback that hinders performance: a low regression rate. An earlier study found that doping the fuel with energetic additives such as aluminium, boron, hydrogen, and ammonia might increase the pace of regression. These nanoparticles will enhance evaporation and combustion efficiency, hence accelerating regression. According to the data, using aluminium increases regression rates by up to 21.2%, followed by using magnesium (19.9%), and iron (8.7%), which has the smallest increase in regression rates. According to this study, adding energetic materials to the fuel of hybrid rocket motors has improved the regression rate problem.
References
M. Bouziane, A. E. M. Bertoldi, P. Milova, P. Hendrick, and M. Lefebvre, “Performance comparison of oxidizer injectors in a 1-kN paraffin-fueled hybrid rocket motor,” Aerosp. Sci. Technol., vol. 89, pp. 392–406, 2019.
Y. Wu et al., “Experimental investigation of fuel composition and mix-enhancer effects on the performance of paraffin-based hybrid rocket motors,” Aerosp. Sci. Technol., pp. 620–627, 2018.
D. Pastrone, “Approaches to low fuel regression rate in hybrid rocket engines,” Int. J. Aerosp. Eng., vol. 2012, no. ii, 2012.
M. Z. Akhter and M. A. Hassan, “Energetic additives for hybrid rocket propulsion - Review,” 2020 Adv. Sci. Eng. Technol. Int. Conf. ASET 2020, pp. 1–6, 2020, doi: 10.1109/ASET48392.2020.9118206.
S. Zhang, F. Hu, and W. Zhang, “Numerical investigation on the regression rate of hybrid rocket motor with star swirl fuel grain,” Acta Astronaut., vol. 127, pp. 384–393, 2016.
D. Lee and C. Lee, “Hybrid gas generator for a staged hybrid rocket engine,” J. Propuls. Power, vol. 33, no. 1, pp. 204–212, 2017.
L. lin Liu, X. He, Y. Wang, Z. bin Chen, and Q. Guo, “Regression rate of paraffin-based fuels in hybrid rocket motor,” Aerosp. Sci. Technol., vol. 107, 2020.
G. A. Risha, “Enhancement of Hybrid Rocket Combustion Performance UsingNano-Sized Energetic Particles,” Ph.D. Diss. Pennsylvania State Univ. PA, Park, 2003, [Online]. Available: http://ieeeauthorcenter.ieee.org/wp-content/uploads/IEEE-Reference-Guide.pdf.
G. A. Risha, B. J. Evans, E. Boyer, and K. K. Kuo, “Metals, Energetic Additives, and Special Binders Used in Solid Fuels for Hybrid Rockets,” AIAA J., pp. 413–456, 2007.
C. Carmicino and A. R. Sorge, “Experimental Investigation into the Effect of Solid-Fuel Additives on Hybrid Rocket Performance,” J. Propuls. POWER, vol. 2, no. 31, pp. 699–713, 2015.
M. J. Chiaverini and K. K. Kuo, “Fundamentals of Hybrid Rocket Combustion and Propulsion,” AIAA J., vol. 218, 2007.
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