Faculty Member, Department of Space Sciences, Aerospace Systems Research Institute, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran


Monopropellant thruster of atitude control system is a requirement for the development and functionalization of satellites in space, which have expensive and high-tech technology. Hydrazine thrusters are currently the most widely used thrusters for guidance and control systems of re-entry and manned spacecraft. In this paper, design and computation of an injector with hollow-cone spray with two tangential inlets as a fuel injector of a 10N monopropellant hydrazine thruster is presented. This injector has designed based on Bazarov method so that can generate a spray with a common (not so big) spray angle and very thin liquid sheet. Therefore it will be suitable from aspect of limitation of  the catalyst bed length and also gives finer atomization.The phenomenon of creating and developing an air core in the internal flow of these injectors and its simulation is complex due to the existence of two turbulent swirl flows in two different phases, liquid and gas, which have an interface. For this injector, simulation of the internal flow has been performed to predict the output flow characteristics and ensure the formation of the gas core inside it. These characteristics include the spray cone angle, liquid sheet thickness, the output velocity distribution of the injector nozzle, and etc. For this purpose, volume of fluid (VOF) method has been used and flow turbulence has been simulated using the k-emodel. The results of this study is presented in detail in the paper.


[1]     Yang, A.S., “Satellite Hydrazine Propulsion System Design Trades”, Journal of Da-Yeh University, 10, 2001, PP. 41-50.
[2]     Bayvel, z., L. Orzechovski, Liquid Atomization, Taylor & Francis, 1993.
[3]     Chinn, J., “The Internal Flow And Exit Conditions of Pressure Swirl Atomizers,” Atomization Spray, 10, 2000, pp. 121-146.
[4]     Cooper, D. and Yule, A. J. “Waves on The Air Core/Liquid Interface of A Pressure Swirl Atomizer.” Proc., 17th ILASS-Europe, Switzerland, Zurich, 2001, pp. 105-115.
[5]     Buelow, Ph. E. O. and Mao, S., Smith, Ch. and Bretz, D., “Two-phase Computational Fluid Dynamics Analysis Applied to Prefilming Pure-Airbalast Atomizer,” Journal of Propulsion and Power, Vol. 19, 2003, pp. 235-241.
[6]     R. El-Sayed Negeed, S. Hidaka, M. Kohno, Y. Takata, “Experimental and Analytical Investigation of Liquid Sheet Breakup Characteristics”, International Journal of Heat and Fluid Flow, Vol. 32, 2011, pp. 95–106.
[7]     K.Y. Huh, E. Lee, J.Y. Koo, "Diesel Spray Atomization Model Considering Nozzle Exit Turbulence Conditions", Atomization and Sprays, Vol. 8, 1998, pp. 453-469.
[8]     Sarre C.K., Kong S.C., Reitz R.D., "Modeling the Effects of Injector Nozzle Geometry on Diesel Sprays", SAE Congress, 1999.
[9]     K. Y. Huh, A.D. Gosman, "A Phenomenological Model of Diesel Spray Atomization," Pr International Conference on Multiphase Flows, Tsukuba, Japan, 1991.
[10]  Klein M., Sadiki A., "A Digital Filter Based Generation of Inflow Data for Spatially Developing Direct Numerical or Large Eddy Simulations", J. Computational Physics, Vol. 186, 2003, pp. 652-665.
[11]  Trinh H.P., Chen C.P., Balasubramanyan M.S., "Numerical Simulation of Liquid Jet Atomization Including Turbulence Effects", J. Engineering for Gas Turbines and Power, Vol. 129, 2007, pp. 920-928.
[12]  Trinh. Huu, "Modeling of Turbulence Effect on Liquid Jet Atomization", Phuoc ProQuest Dissertations and Theses, 2004.
[13]  Trinh Huu P., Chen C. P., "Modeling of Turbulence Effects on Liquid Jet Atomization and Breakup", 43rd AIAA Aerospace Sciences Meeting and Exhibit, 2005.
[14]  Bordas, R., John, V., Schmeyer, E., and Thevenin, D., “Measurement and Simulation of A Droplet Population in a Turbulent Flow Field.” Comput. Fluids, 66, 2012, pp. 52-62.
[15]  Reddy, R., and Banerjee, R., “GPU Accelerated VOF Based Multiphase Flow Solver And Its Application To Sprays.” Comput. Fluids, 117, 2015, pp. 287-303.
[16]  Grosshans, H., Szasz, R. Z., and Fuchs, L., “Enhanced Liquid–Gas Mixing Due To Pulsating Injection.” Comput. Fluids, 107, 2015, pp. 196-204.
[17]  Movahednejad, E., Ommi, F. and Hosseinalipour, S. M., "Prediction of Droplet Size and Velocity Distribution in Droplet Formation Region of Liquid Spray", Entropy, 12, 2010, pp. 1484-1498 .
[18]  Hosseinalipour, S. M., Karimaei, H., Ghorbani, R., “Study The Y-Atomizer Performance Of A Power Plant in Order to Extract Mean Droplet Diameter Range”, 2nd Proceeding of Gas Turbine, Iran University of Science and Technology, Tehran, 29–30 May 2013 (in Persian).
[19]  Hosseinalipour, S.M., Karimaei, H. and Ommi, F., “Numerical Study The Effect of Mass flow Rate on Liquid Sheet Properties ResultingfromASwirlInjector”, 3nd Proceeding of Gas Turbine, Iran University of Science and Technology, Tehran, 13–15 May 2014 (in Persian).
[20]  Hosseinalipour, S. M. and Karimaei, H., “A New Model Based on Coupling of MEP/CFD/ILIA for Prediction of Primary Atomization”, Canadian Journal of Chemical Engineering, 94, 2016, pp. 792-802.
[21]  Hosseinalipour, S. M. and Karimaei, H., Movahednejad, E. and Ommi, F., “Application of Maximum Entropy Principle for Estimation of Droplet-Size Distribution Using Internal Flow Analysis of a Swirl Injector”, International Journal of  Spray and Combustion Dynamic, 8, 2016, pp. 205-216.
[22]  F. Ommi., “Space Propulsion and Rocket”, Besat Publication, 2009. (in persian)
[23]  Shankar, V. and Anantha Ram, K., “Experimental Investigations of The 10 N Catalytic Hydrazine Thruster”, Acta Astronautica, 12, 1985, pp. 237-249.
[24]  Ansys-Fluent Software Version 15, “Fluent’s User’s Guide” , 2015.