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1(4), (2022):13-19. DOI: http://doi.org/10.46632/jame/1/4/3
Atri Bandyopadhyay, Ankit Kumar Mishra
The current research is focused on understanding the propulsive parameters of hybrid rocket motors. A comparative study is prepared from various research papers. The fuels paraffin wax, hydroxyl-terminated polybutadiene (HTPB) and polymethyl methacrylate (PMMA) with added additives (Al/Mg) were combined with two oxidizers, liquid oxygen (LOX), nitrous oxide (N2O). The propulsive parameters examined were the combustion efficiency, combustion or adiabatic flame temperature, characteristics velocity and regression rate. The propellant pair paraffin-N2O provided the highest performance for all parameters studied. This study provides an advantageous propellant option for future rocket propulsion based on a comparative investig
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Adam Okninski, Wioleta Kopacz, Damian Kaniewski, Kamil Sobczak,Hybrid rocket propulsion technology for space transportation revisited – propellant solutions and challenges. https://doi.org/10.1016/j.fpc.2021.11.015.
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Mariana Conti Tarifa, Loreto Pizzuti, São Bernardo do Campo, São Bernardo do Campo, THEORETICAL PERFORMANCE ANALYSIS OF HYBRID ROCKET PROPELLANTS AIMING AT THE DESIGN OF A TEST BENCH AND A PROPULSIVE SYSTEM. DOI: 10.13009/EUCASS2019-488
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ZezhongWang, XinLin, FeiLi andXilongYu, Combustion performance of a novel hybrid rocket fuel grain with a nested helical structure. https://doi.org/10.1016/j.ast.2019.105613
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Atri Bandyopadhyay, Ankit Kumar Mishra, ” Comparative Study on Hybrid Rocket Fuels for Space Launch Vehicles Moving in Higher Orbits”, REST Journal on Advances in Mechanical Engineering, 1(4), (2022):13-19.