[1] T. Hiraiwa, T. Saito, T. Tomita, N Azuma, K. Okita, K. Obase, and T. Kaneko, “Research works of ethanol propulsion system for the future rocket-plane experimental vehicle” 47th AIAA/ASME/ SAE/ASEE Joint Propulsion Conference & Exhibition, p.6114, 2011.
[2] K. Sakaki, T. Funahashi, S. Nakaya, M. Tsue, R. Kanai, K. Suzuki, T. Inagawa, and T. Hiraiwa, “Longitudinal combustion instability of a pintle injector for a liquid rocket engine combustor”. Combustion and Flame, Vol. 194: pp. 115-12, 2018.
[3] R. Woodard, K. Miller, V. Bazarov, G. Gurin, S. Pal, and R. Santoro “Injector research for Shuttle OMS upgrade using LOX/ethanol propellants” In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibition, p.3816, 1998.
[4] C. Bach, J. Sieder, O. Przybliski, and M. Tajmar, “Smart Rockets: Development of a 500 N LOX-Ethanol-Sounding rocket for the DLR STERN programme”, In 62th Conference: German Aerospace Congress, Stuttgart, pp.1-10, 2013.
[5] K. Sakaki, M. Choi, S. Nakaya, M. Tsue, and T. Hiraiwa, “Fundamental combustion characteristics of ethanol/liquid oxygen rocket engine combustor with planar pintle-type injector”, Transactions of the Japan Society for Aeronautical and Space Sciences, Vol. 58, No.1, pp. 15-22, 2015.
[6] J. Sieder, K. Kleebusch, C. Bach, and M. Tajmar, “Development history and verification of the flight model of a 500 N Ethanol/LOX rocket engine”, In 7th European Conference for Aeronautics and sapce Sciences, Milan ,Italy, pp.3-6, 2017.
[7] R. Delpy and J. Oswald, “PERSEUS project 5 kN LOX/Ethanol rocket engine fire tests” , 7th European Conference for Aeronautics and Aerosapce Sciences, (EUCASS), 2017.
[8] S. M.R. Mahmoudian, H. Ghasemi, and A.R. Toloei, “The process of designing and manufacturing a prototype space thruster with oxygen-crocin cryogenic propellant,” The 10th conference of the Iranian Aerospace Association, Tehran, 2019 (in Persian).
[9] D. Ramesh, S. Khodadadiyan, and H. Karimi, “
Optimization of Schematic and Parameters of Staged Combustion Launch Vehicle Liquid Engines”,
Journal of Space Science and Technology, Vol.9, No.1, pp. 1-11, 2016. (in Persian).
[10] A.H. Edalatpour, F. Ommi, Z. Saboohi, “
Performance Analysis of Liquid Propellant Micro-propulsion with Liquid Oxygen as Cryogenic Oxidizer” ,
Journal of Space Science and Technology, Vol.12, No.1, pp. 23-40, 2019.(in Persian).
[11] S. Gordon, and B. J. McBride, Computer Program for Calculation of Complex Chemical Equilibrium Compositions, Rocket Performance, Incident and Reflected Shocks, and Chapman-Jouguet Detonations, NASA SP-273, 1976.
[12] D. K. Huzel, and D. H. Huang, “Modern Engineering for Design of Liquid Propellant Rocket Engines, (Revised and enlarged edition)”, AIAA Progress in Astronautics and Aeronautics, Washington, DC: American Institute of Aeronautics and Astronautics, Vol. 147, 1992.
[13] R. W. Humble, h. N. Gary, and W. J. Larson, Space Propulsion Analysis and Design, McGraw-Hill, 1995.
[14] G. Dressler, and J. Bauer, “TRW pintle engine heritage and performance characteristics” In 36th AIAA/ASME/ SAE/ ASEE joint propulsion conference and exhibit, Las Vegas, NV, U.S.A., p.3871,2000.
