참고문헌 (38)

1. J. Propuls. Power George 17 35 2001 10.2514/2.5704 Fuel regression rate in hydroxyl-terminated-polybutadiene/gaseous-oxygen hybrid rocket motors 

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2. J. Propuls. Power Carmicino 21 606 2005 10.2514/1.9945 Role of injection in hybrid rockets regression rate behaviour 

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3. Chin. J. Aeronaut. Tian 27 1343 2014 10.1016/j.cja.2014.08.016 Transient simulation of regression rate on thrust regulation process in hybrid rocket motor 

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4. Acta Astronaut. Sun 126 325 2016 10.1016/j.actaastro.2016.04.029 Diameter and position effect determination of diaphragm on hybrid rocket motor 

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5. Acta Astronaut. Cai 128 83 2016 10.1016/j.actaastro.2016.07.002 Effect of grain port length-diameter ratio on combustion performance in hybrid rocket motors 

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6. Aerosp. Sci. Technol. Cai 24 141 2013 10.1016/j.ast.2011.11.001 Scale effect of fuel regression rate in hybrid rocket motor 

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7. J. Propuls. Power Bianchi 32 984 2016 10.2514/1.B36000 Hybrid rockets with axial injector: port diameter effect on fuel regression rate 

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8. J. Propuls. Power Bianchi 31 919 2015 10.2514/1.B35587 Simulation of gaseous oxygen/hydroxyl-terminated polybutadiene hybrid rocket flowfields and comparison with experiments 

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9. J. Propuls. Power Kim 29 573 2013 10.2514/1.B34619 Regression characteristics of the cylindrical multiport grain in hybrid rockets 

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10. Acta Astronaut. Swami 52 619 2003 10.1016/S0094-5765(02)00126-1 Analysis and testing of similarity and scale effects in hybrid rocket motors 

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11. Lee 5754 2011 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit Combustion characteristics of initial port diameter variation of solid fuel in hybrid rocket motor 

12. J. Aerosp. Technol. Manag. Kafafy 6 69 2014 10.5028/jatm.v6i1.268 Effect of varying design options on the transient behavior of a hybrid rocket motor 

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13. Int. J. Turbomach. Propuls. Power Berwal 5 12 2020 10.3390/ijtpp5020012 Experimental investigation on combustion characteristics of hybrid rocket fuels with multi-angle diverging injector 

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14. Bettner 1998 Polyethylene and Hydrogen Peroxide Hybrid Testing at the United States Air Force Academy 

15. J. Propuls. Power Fraters 32 958 2016 10.2514/1.B35485 Experimental characterization of combustion instabilities in high-mass-flux hybrid rocket engines 

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16. Sci. China, Technol. Sci. Rao 55 125 2012 10.1007/s11431-011-4597-4 Design and optimization of variable thrust hybrid rocket motors for sounding rockets 

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17. J. Propuls. Power Farbar 23 476 2007 10.2514/1.22091 Investigation of metallized and nonmetallized hydroxyl terminated polybutadiene/hydrogen peroxide hybrid rockets 

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18. J. Propuls. Power Jung 30 514 2014 10.2514/1.B34739 Autoignitable and restartable hybrid rockets using catalytic decomposition of an oxidizer 

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19. J. Propuls. Power Ahn 34 1189 2018 10.2514/1.B36949 Design of multiport grain with hydrogen peroxide hybrid rocket 

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20. Acta Astronaut. Wei 164 334 2019 10.1016/j.actaastro.2019.07.020 Experimental investigation of the effect of nozzle throat diameter on the performance of a hybrid rocket motor with swirling injection of high-concentration hydrogen peroxide 

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21. Kwon 2013 2013 Asia Pacific International Symposium on Aerospace Technology, APISAT Comparison between paraffin and polyethylene in hybrid thruster with catalytically decomposed hydrogen peroxide 

22. Kang 4864 2016 52nd AIAA/SAE/ASEE Joint Propulsion Conference Design and performance evaluation of hybrid rocket using 95 wt.% H2O2 

23. Gordon 1994 Computer program for calculation of complex chemical equilibrium compositions and applications. Part 1: Analysis 

24. Aerosp. Sci. Technol. Yun 2020 10.1016/j.ast.2020.105823 Integration validation of key components for small sounding rockets 

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25. Aerosp. Sci. Technol. Bouziane 89 392 2019 10.1016/j.ast.2019.04.009 Performance comparison of oxidizer injectors in a 1-kN paraffin-fueled hybrid rocket motor 

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26. Huang 1992 Modern engineering for design of liquid-propellant rocket engines 

27. J. Propuls. Power An 27 422 2011 10.2514/1.48939 Chugging instability of H2O2 monopropellant thrusters with reactor aspect ratio and pressures 

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28. J. Propuls. Power An 25 1041 2009 10.2514/1.40822 Scaling and evaluation of Pt/Al2O3 catalytic reactor for hydrogen peroxide monopropellant thruster 

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29. Aerosp. Sci. Technol. Jo 60 1 2017 10.1016/j.ast.2016.10.022 Response characteristics of H2O2 monopropellant thrusters with MnO2-mixed PbO catalyst 

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30. J. Propuls. Power Jo 27 920 2011 10.2514/1.B34222 Chugging instability of H2O2 monopropellant thrusters with catalyst reactivity and support sizes 

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31. Aerosp. Sci. Technol. Heo 78 26 2018 10.1016/j.ast.2018.03.032 Effect of dual-catalytic bed using two different catalyst sizes for hydrogen peroxide thruster 

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32. Flow Meas. Instrum. Ghassemi 22 406 2011 10.1016/j.flowmeasinst.2011.05.001 Application of small size cavitating venturi as flow controller and flow meter 

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33. Exp. Therm. Fluid Sci. Abdulaziz 53 40 2014 10.1016/j.expthermflusci.2013.10.010 Performance and image analysis of a cavitating process in a small type venturi 

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34. Kearney 6144 2007 AIAA Space 2007 Conference & Exposition Improvements to the marketability of hybrid propulsion technologies 

35. Marxman 371 1963 Symposium (International) on Combustion Turbulent boundary layer combustion in the hybrid rocket 

36. Int. J. Aerosp. Eng. Pastrone 2012 2012 10.1155/2012/649753 Approaches to low fuel regression rate in hybrid rocket engines 

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37. Aerosp. Sci. Technol. Tian 42 334 2015 10.1016/j.ast.2015.01.015 Ignition theory investigation and experimental research on hybrid rocket motor 

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38. Taylor 1997 Introduction to error analysis, the study of uncertainties in physical measurements 

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