[3] G. P. Sutton and O. Biblarz, Rocket propulsion elements. John Wiley & Sons, 2016.

7 References

[1] “Sciencedaily, Retrieved Nov 02, 2018, from https://www.sciencedaily.com”.

[2] W. J. Larson, G. N. Henry, and R. W. Humble, Space propulsion analysis and design. McGraw-Hill, 1995.

[3] G. P. Sutton and O. Biblarz, Rocket propulsion elements. John Wiley & Sons, 2016.

[4] C. Carmicino, F. Scaramuzzino, and A. R. Sorge, “Trade-off between paraffin-based and aluminium-loaded HTPB fuels to improve performance of hybrid rocket fed with N

O,” Aerosp. Sci. Technol., vol. 37, pp. 81–

92, 2014.

[5] “SPACE , Retrieved May 21, 2019, from https://www.space.com/16769-spaceshipone-first-private- spacecraft.html”.

[6] “SPACE NEWS, Retrieved May 21, 2019, from Https://spacenews.com/spaceshiptwo-flies-to-the-edge-of- space-again/”.

[7] “SkyRocket, Retrived May 21, 2019, from https://space.skyrocket.de/doc_sat/ss2_hist.htm”.

[8] D. Altman, “Hybrid rocket development history,” in 27th Joint Propulsion Conference, 1991, p. 2515.

[9] G. Marxman and M. Gilbert, “Turbulent boundary layer combustion in the hybrid rocket,” in Symposium (International) on Combustion, 1963, vol. 9, no. 1, pp. 371–383.

[10] G. A. Marxman, C. E. Wooldridge, and R. J. Muzzy, “Fundamentals of hybrid boundary-layer combustion,”

in Progress in Astronautics and Rocketry, vol. 15, Elsevier, 1964, pp. 485–522.

[11] G. A. Marxman, “Combustion in the turbulent boundary layer on a vaporizing surface,” in Symposium (International) on Combustion, 1965, vol. 10, no. 1, pp. 1337–1349.

[12] G. A. MARXMAN and C. E. WOOLRIDGE, “Research on the combustion mechanism of hybrid rockets(Hybrid rockets combustion mechanism, discussing turbulent boundary layer with heat and mass transfer, chemical reactions, etc),” 1968.

[13] G. A. Marxman, “Boundary-layer combustion in propulsion,” in Symposium (international) on Combustion, 1967, vol. 11, no. 1, pp. 269–289.

[14] C. E. Woolridge, G. Marxman, and R. J. Kier, “Investigation of combustion instability in hybrid rockets,”

NASA Contract NAS 1-7310, Stanford Res. Inst., Stanford Univ., Stanford, CA, 1969.

[15] R. Muzzy, “Applied hybrid combustion theory,” in 8th Joint Propulsion Specialist Conference, 1972, p. 1143.

[16] R. J. Muzzy and C. E. Wooldridge, “Internal ballistic considerations in hybrid rocket design.,” J. Spacecr.

Rockets, vol. 4, no. 2, pp. 255–262, 1967.

[17] M. Chiaverini, “Review of solid-fuel regression rate behavior in classical and nonclassical hybrid rocket motors,” Prog. Astronaut. Aeronaut., vol. 218, p. 37, 2007.

[18] L. Lees, “Convective heat transfer with mass addition and chemical reactions,” in Combustion and Propulsion, Third AGARD Colloquium, 1958, pp. 451–498.

[19] H. Schlichting and K. Gersten, Boundary-layer theory. Springer, 2016.

[20] D. Altman and R. W. Humble., “Hybrid Rocket Propulsion Systems,” in Space Propulsion Analysis and Design, 1995, pp. 403–441.

[21] G. Risha et al., “Pyrolysis and combustion of solid fuels in various oxidizing environments,” in 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, p. 3184.

[22] P. George, S. Krishnan, P. M. Varkey, M. Ravindran, and L. Ramachandran, “Fuel regression rate in hydroxyl- terminated-polybutadiene/gaseous-oxygen hybrid rocket motors,” J. Propuls. Power, vol. 17, no. 1, pp. 35–

42, 2001.

[23] L. D. Smoot, “Regression rate of nonmetalized hybrid fuel system,” AIAA J., vol. 3, no. 8, pp. 1408–1413,

1965.

[24] J. Y. Lestrade, J. Messineo, J. Hijlkema, P. Prévot, G. Casalis, and J. Anthoine, “Hybrid chemical engines:

recent advances from sounding rocket propulsion and vision for spacecraft propulsion,” AerospaceLab J., vol.

11, pp. 14--pages, 2016.

[25] D. Altman and A. Holzman, “Overview and history of hybrid rocket propulsion,” Prog. Astronaut. Aeronaut., vol. 218, p. 1, 2007.

[26] F. Barato, “Numerical and Experimental Investigation of Hybrid Rocket Motors Transient Behavior,” PhD dessertation, Padova Univercity, Center of Studies and Activities (CISAS), Padova, Italy, 2013.

[27] J. Nijsse, “Numerical Modelling of Staged Combustion Aft-Injected Hybrid Rocket Motors,” PhD dessertation, Graduate Department of Aerospace Science and Engineering, University of Toronto, 2012.

[28] M. Boiocchi, L. Galfetti, and L. Di Landro, “Parffin-Based Solid Fuels for Hybrid Propolsion Filled With Lithium Aluminium Hydride: Thermal, Mechanical, and Ballistic Characterization,” Int. J. Energ. Mater.

Chem. Propuls., vol. 15, no. 6, 2016.

[29] M. Karabeyoglu, B. Cantwell, and D. Altman, “Development and testing of paraffin-based hybrid rocket fuels,” in 37th Joint Propulsion Conference and Exhibit, 2001, p. 4503.

[30] M. A. Karabeyoglu, D. Altman, and B. J. Cantwell, “Combustion of liquefying hybrid propellants: Part 1, general theory,” J. Propuls. Power, vol. 18, no. 3, pp. 610–620, 2002.

[31] M. A. Karabeyoglu and B. J. Cantwell, “Combustion of liquefying hybrid propellants: Part 2, Stability of liquid films,” J. Propuls. Power, vol. 18, no. 3, pp. 621–630, 2002.

[32] M. A. Dornheim, “Ideal hybrid fuel is... wax?,” Aviat. week Sp. Technol., vol. 158, no. 5, pp. 52–54, 2003.

[33] C. Carmicino and A. R. Sorge, “Performance comparison between two different injector configurations in a hybrid rocket,” Aerosp. Sci. Technol., vol. 11, no. 1, pp. 61–67, 2007.

[34] C. Carmicino and A. R. Sorge, “Role of injection in hybrid rockets regression rate behaviour,” J. Propuls.

power, vol. 21, no. 4, pp. 606–612, 2005.

[35] T. Boardman, D. Brinton, R. Carpenter, and T. Zoladz, “An experimental investigation of pressure oscillations and their suppression in subscale hybrid rocket motors,” in 31st Joint Propulsion Conference and Exhibit, 1995, p. 2689.

[36] A. H. Lefebvre and V. G. McDonell, Atomization and sprays. CRC press, 2017.

[37] W. H. Knuth, M. J. Chiaverini, D. J. Gramer, and J. A. Sauer, “Solid-Fuel Regression Rate Behavior of Vortex Hybrid Rocket Engines,” J. Propuls. Power, vol. 18, no. 3, pp. 600–609, 2002.

[38] W. Knuth, D. Gramer, M. Chiaverini, and J. Sauer, “Development and testing of a vortex-driven, high- regression rate hybrid rocket engine,” in 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, p. 3507.

[39] W. Knuth, D. Gramer, M. Chiaverini, J. Sauer, R. Whitesides, and R. Dill, “Preliminary CFD analysis of the vortex hybrid rocket chamber and nozzle flow field,” in 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, p. 3351.

[40] W. Knuth, M. Chiaverini, D. Gramer, and J. Sauer, “Experimental investigation of a vortex-driven high- regression rate hybrid rocket engine,” in 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, p. 3348.

[41] T. Takashi, S. Yuasa, and K. Yamamoto, “Effects of swirling oxidizer flow on fuel regression rate of hybrid rockets,” in 35th Joint Propulsion Conference and Exhibit, 1999, p. 2323.

[42] S. Yuasa, O. Shimada, T. Imamura, T. Tamura, and K. Yamoto, “A technique for improving the performance of hybrid rocket engines,” in 35th Joint Propulsion Conference and Exhibit, 1999, p. 2322.

[43] N. Bellomo, F. Barato, M. Faenza, M. Lazzarin, A. Bettella, and D. Pavarin, “Numerical and experimental

investigation of unidirectional vortex injection in hybrid rocket engines,” J. Propuls. Power, vol. 29, no. 5,

pp. 1097–1113, 2013.

[44] C. P. Kumar and A. Kumar, “Effect of swirl on the regression rate in hybrid rocket motors,” Aerosp. Sci.

Technol., vol. 29, no. 1, pp. 92–99, 2013.

[45] C. Carmicino and A. R. Sorge, “Influence of a conical axial injector on hybrid rocket performance,” J. Propuls.

Power, vol. 22, no. 5, pp. 984–995, 2006.

[46] J. Pucci, “The effects of swirl injector design on hybrid flame-holding combustion instability,” in 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002, p. 3578.

[47] A. E. de Morais Bertoldi, C. A. G. Veras, and P. Hendrick, “Experimental Evaluation of Pressure-Swirl Injection System over Solid Fuel Regression Rate in Hybrid Rockets,” in 2017 EUCASS Conference, 2017, p. 661.

[48] A. E. de Morais Bertoldi, M. Bouziane, C. A. G. Veras, J. Lee, and M. V. C. Costa, “Experimental Investigation of the Feed System Instabilities in Hybrid Rocket Motors,” in 69th International Astronautical Congress (IAC), 2018.

[49] A. E. De Morais Bertoldi, “Combustion Instability in Hybrid Rocket Propulsion Systems,” PhD Dissertation, Mechanical Engineering Department, University of Brasília, Brasília, DF, Brazil, July 2018. In Portuguese.

[50] M. A. Karabeyoglu, B. J. Cantwell, and G. Zilliac, “Development of scalable space-time averaged regression rate expressions for hybrid rockets,” J. Propuls. Power, vol. 23, no. 4, pp. 737–747, 2007.

[51] Brian J. Cantwell, “Wax Fuel Gives Hybrid Rockets More Oomph”.

[52] A. Chandler, E. Jens, B. Cantwell, and G. S. Hubbard, “Visualization of the liquid layer combustion of paraffin fuel for hybrid rocket applications,” in 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2012, p. 3961.

[53] “EXPLO5, Retrieved from http://www.ozm.cz/en/explo-5-software/, (accesed 23-07-2018)”.

[54] M. J. Chiaverini and K. K. Kuo, Fundamentals of Hybrid Rocket Combustion and Propulsion. American Institute of Aeronautics and Astronautics, 2007.

[55] B. Genevieve, M. Brooks, J. de la Beaujardiere, and L. Roberts, “Performance Modeling of a Paraffin Wax/Nitrous Oxide Hybrid Rocket Motor,” in 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011, p. 420.

[56] A. Karabeyoglu, G. Zilliac, B. J. Cantwell, S. DeZilwa, and P. Castellucci, “Scale-up tests of high regression rate paraffin-based hybrid rocket fuels,” J. Propuls. Power, vol. 20, no. 6, pp. 1037–1045, 2004.

[57] T. R. Brown and M. C. Lydon, “Testing of Paraffin-Based Hybrid Rocket Fuel Using Hydrogen Peroxide Oxidizer,” in AIAA Region 5 Student Conference, Wichita, USA, 2005.

[58] “RPA, Rocket Propulsion Analysis, Retrieved from http://propulsion-analysis.com/index.htm, (accesed 15- 06-2019)”.

[59] 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.

[60] C. Carmicino and A. R. Sorge, “Role of injection in hybrid rockets regression rate behaviour,” J. Propuls.

Power, vol. 21, no. 4, pp. 606–612, 2005.

[61] D. Bianchi, F. Nasuti, and C. Carmicino, “Hybrid rockets with axial injector: port diameter effect on fuel regression rate,” J. Propuls. Power, vol. 32, no. 1, pp. 984–996, 2016.

[62] F. Scaramuzzino, C. Carmicino, G. Festa, A. Viviani, and A. Russo, “Fuel regression-rate characterization on a lab-scale hybrid rocket burning N2O and paraffin-based propellants,” in 49th AIAA/ASME/SAE/ASEE Joint PropulsionConference, 2013, p. 4039.

[63] D. Bianchi, F. Nasuti, and C. Carmicino, “Numerical Analysis of Port Diameter Effect on Hybrid Rocket Fuel

Regression Rate with Axial Injection,” in 51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015, p. 3835.

[64] C. Carmicino and D. Pastrone, “Novel Comprehensive Technique for Hybrid Rocket Experimental Ballistic Data Reconstruction,” J. Propuls. Power, vol. 34, no. 1, pp. 133–145, 2017.

[65] E. Toson and A. M. Karabeyoglu, “Design and Optimization of Hybrid Propulsion Systems for In-Space Application,” in 51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015, p. 3937.

[66] M. Invigorito, G. Elia, and M. Panelli, “An Improved Approach for Hybrid RocNet Injection System Design,”

World Acad. Sci. Eng. Technol. Int. J. Mech. Aerospace, Ind. Mechatron. Manuf. Eng., vol. 10, no. 4, pp. 686–

696, 2016.

[67] E. Doran, J. Dyer, K. Lohner, Z. Dunn, B. Cantwell, and G. Zilliac, “Nitrous oxide hybrid rocket motor fuel regression rate characterization,” in 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2007, p. 5352.

[68] H. Silva Couto, P. T. Lacava, D. Bastos-Netto, and A. P. Pimenta, “Experimental evaluation of a low pressure- swirl atomizer applied engineering design procedure,” J. Propuls. Power, vol. 25, no. 2, pp. 358–364, 2009.

[69] M. Badami, V. Bevilacqua, F. Millo, M. Chiodi, and M. Bargende, “GDI swirl injector spray simulation: a combined phenomenological-CFD approach,” 2004.

[70] V. Zakirov, M. Sweeting, T. Lawrence, and J. Sellers, “Nitrous oxide as a rocket propellant,” Acta Astronaut., vol. 48, no. 5–12, pp. 353–362, 2001.

[71] N. K. Rizk and A. H. Lefebvre, “Internal flow characteristics of simplex swirl atomizers,” J. Propuls. Power, vol. 1, no. 3, pp. 193–199, 1985.

[72] A. R. Jones, “Design optimization of a large pressure-jet atomizer for power plant,” Proc. 2nd ICLASS, Madison, Wis., 1982, pp. 181–185, 1982.

[73] A. H. Lefebvre and J. Ortman, “Fuel distributions from pressure-swirl atomizers,” J. Propuls. Power, vol. 1, no. 1, pp. 11–15, 1985.

[74] G. Cai, P. Zeng, X. Li, H. Tian, and N. Yu, “Scale effect of fuel regression rate in hybrid rocket motor,”

Aerosp. Sci. Technol., vol. 24, no. 1, pp. 141–146, 2013.

[75] D. R. Greatrix, “Regression rate estimation for standard-flow hybrid rocket engines,” Aerosp. Sci. Technol., vol. 13, no. 7, pp. 358–363, 2009.

[76] Hall. N, “(2015 May 05),” Specific Impulse, Retrieved from https://www.grc.nasa.gov/WWW/K- 12/airplane/specimp.htmlr, (accesed 23-04-2019).

[77] Q. Zhang, Z. Wei, W. Su, J. Li, and N. Wang, “Theoretical modeling and numerical study for thrust-oscillation characteristics in solid rocket motors,” J. Propuls. Power, vol. 28, no. 2, pp. 312–322, 2012.

[78] H. Li, L. Ye, X. Wei, T. Li, and S. Li, “The design and main performance of a hydrogen peroxide/kerosene coaxial-swirl injector in a lab-scale rocket engine,” Aerosp. Sci. Technol., vol. 70, pp. 636–643, 2017.

[79] B. Greiner and R. Frederick JR, “Hybrid rocket instability,” in 29th Joint Propulsion Conference and Exhibit, 1993, p. 2553.

[80] B. Greiner and R. FREDERICK JR, “Results of labscale hybrid rocket motor investigation,” in 28th Joint Propulsion Conference and Exhibit, 1992, p. 3301.

[81] E. Gamper and R. Hink, Design and test of nitrous oxide injectors for a hybrid rocket engine. Deutsche Gesellschaft für Luft-und Raumfahrt-Lilienthal-Oberth eV, 2013.

[82] G. Cai, Y. Zhang, H. Tian, P. Wang, and N. Yu, “Effect of grain port length--diameter ratio on combustion performance in hybrid rocket motors,” Acta Astronaut., vol. 128, pp. 83–90, 2016.

[83] A. Karabeyoglu, “Lecture 10 Hybrid Rocket propulsion Design Issues,” AA 284a Adv. Rocket Propulsion, AAE Dep. Stanford Univ., p. 18, 2012.

[84] R. D. Swami and A. Gany, “Analysis and testing of similarity and scale effects in hybrid rocket motors,” Acta Astronaut., vol. 52, no. 8, pp. 619–628, 2003.

[85] A. Karabeyoglu, “Lecture 10 Hybrid Rocket propulsion Design Issues,” AA 284a Adv. Rocket Propulsion,

AAE Dep. Stanford Univ., p. 18, 2012.

[86] D. Pastrone, “Approaches to low fuel regression rate in hybrid rocket engines,” Int. J. Aerosp. Eng., vol. 2012,

2012.