Iranian Chemical Engineering Journal

Iranian Chemical Engineering Journal

Comparing and Investigating the Performance of Iridium-Substituted Nickel Catalyst Gamma-Alumina Base in the Heterogeneous Decomposition Reaction of Hydrazine and Ammonia with the Application of Space Propulsion Systems

Document Type : Original Article

Authors
1 Department of Chemical Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran
2 Department of Chemical Engineering Malek Ashtar University of Technology
Abstract
In this research, the heterogeneous decomposition reaction of hydrazine and ammonia in a space propulsion system of hydrazine monopropellant type with an adiabatic fixed bed reactor and 30% iridium catalyst is used to create a thrust force of 5 newtons and a specific impulse of 220 seconds and the application of position change or orbital motion. This process is created by two heterogeneous reactions and turning into hot light gases of hydrogen and nitrogen leaving the reactor bed and then the nozzle of the thrust force in the opposite direction of
the gas flow. Considering that the iridium 30%
 is a reference and main catalyst that has suitable mechanical, physical, and thermal properties but is very rare and expensive, the purpose of using nickel replacement catalyst 15% is . Compared to iridium, this catalyst is very abundant and cheap, and has functional characteristics, suitable and close to iridium. Regarding the correctness and accuracy of the performance results of two catalysts in a space propulsion system and vacuum conditions and the same static and operational test in a stable and uniform flow of hydrazine to the reactor bed for 30 seconds were measured and evaluated by evaluation indicators such as creating force Thrust (5 newtons), special impulse (about 230 seconds), bed pressure drop (less than 1 bar), minimum amount of ammonia decomposition are compared. Finally, due to the compatibility of nickel catalysts with iridium, a suitable alternative is approved.
Keywords
Subjects

 [1]        Wernimont, J. (2006). System trade Parameter comparison of monopropellants hydrogen peroxide vs hydrazine and others. Joint Propulsion Conference & Exhibit, 9-12.
[2]        Price, T.W. & Evans, D. D. (1968). The status of monopropellant hydrazine technology. National Aerona Utics and Space a Dmini Stration (NAS), Contract No.15, NAS 7-100.
[3]        Schmidt, M. & Zeitschrift. (2013). The decomposition of hydrazine in the Gas phase and over an iridium catalyst. Journal of Physikalische Chemie, 227.
[4]        Escard, J., Ircha, J., Leclbre, C. & Contour J. P. (1973). The state of supported iridium in a hydrazine decomposition catalyst. Journal of Catalysis, 29, 31-39.
[5]        Han, D. I., Han C. Y. & Dong H. S. (2009). Empirical and Co-mutational performance prediction for monopropellant hydrazine thruster employed for satellite. Journal of Spacecraft and Rockets, 46, 6-9.
[6]        Gunter, S. E. & Deppner, H. G. (1989). Modelling and simulation of monopropellant hydrazine thrusters for spacecraft position control. Journal of Chem. Eng. Techno, 8, 426-432.
[7]        Xiaowei, C., Zhang, T., Pinliang, Y., Ming, Z., Weicheng, W., Liangen, X., Xuedong, T. L., Wang, L. & Can, L. (2002). A novel catalyst for hydrazine decomposition: molybdenum carbide supported on. Journal of Chinese Academy of Sciences, P.O. Box 110, Dalian 116023.
[8]        Xiaowei, C. & Zhang, T. (2002). Catalytic decomposition of hydrazine over supported molybdenum nitride catalysts in a monopropellant thruster. Journal of Catalysis letters,79 Nos.
[9]        Oliaee, S. N. (2016). Catalyst development and the stracture dependent properties for hydrazine decomposition. PhD Thesis, A Dissertation Presented to The Graduate Faculty of the University of Akron, United States of America.
[10]      Vieira, R., Bastos, D. T., Netto, M., Ledouxa, J. & Hua, C. P. (2005). Hydrazine decomposition over iridium supported on carbon nanofibers composite for space applications. Journal of Chinese Academy of Sciences, P.O. Box 110, Dalian 116023
[11]      Pakdehi, S. G. & Rasoolzadeh, M. (2015). Comparison of catalytic behavior of iridium and nickel nano catalysts for decomposition of hydrazine. Journal of Procedia Materials, Science 11, 749–753
[12]      Mackled, A. E. & Belal, H. (2009). Modeling of hydrazine decomposition for monopropellant thrusters. Journal of Aerospace Sciences & Aviation Technology (ASAT), 13, 26 – 28
[13]      Tan, A. Y., Prushen, B. D. & Guin, J. A. (1975). Mass transfer in non-uniform packaging. ALChE J., 21, 396
[14]      Satterfield, C.N. (1970). Mass transfer in heterogeneous catalysis, M.I.T. Press Cambridge.
[15]      Shain, S. S. (1961). A note on multi-component publishing. ALChE J., 7, 17.
[16]      Colburn, A. P., & Drew, T. B. (1937). Mass transfer in the catalytic bed. ALChE J., Vol. 33 p.197.
[17]      Ackerman, G. Ver. & Dtsch. (1937). Determination of the heat transfer flux of the fluid flow in the catalyst bed. Eng. Forschungs,382 ,1-8.
[18]      Lewis, W. K., &Whitman, W. (1924). Mass transfer with chemical reactions. Journal of Ind. Eng. Chem.,16 ,12-15.
[20]      Rothfield, L. B. (1963).Concentration fluctuations in a stirred baffled vessel .AIChE J., 9, 19.
[21]      Evans, R. B., Watson B. M. & Mason E. A. (1961). Gaseous diffusion in porous media at uniform pressure. Journal of Chem. Phys., 33, 2076.
[22]      Ebrahim, H., Ghanbari Pakdehi, SH., Alavi, S.A. (2023). Modeling, Design and Testing of Space Thruster Type Hydrazine Monopropellant for the Low Propulsion and the Application of Satellite Status Change. Iranian Chemical Engineering Journal, 21(124), 84-106, [In Persian].
[23]      Kesten, A. S. (1968). Analytical study of catalytic reactors for hydrazine decomposition, Second Annual Progress Report NASA, UARL G910461-24, Contract NAS., 7, 458
[24]      Sanchez, M. M. & Lozano, P. (2015). Monopropellant thrusters: Session12, Aeronautics and Astronautics, 16.522 Space Propulsion Spring.
[25]      Baek, S. W. & Han C. Y. (2012). Effects of catalyst bed failure on thermochemical phenomena for a hydrazine monopropellant thruster using Ir/Al2O3 catalysts. Industrial & Engineering Chemistry Research (I&EC), 51, 5382−5393.
[26]      Wilke, C. R., & Chang, P. (1955). Gaseous Diffusion in Porous Media at Uniform reassure. AIChE J., 1, 264.
[27]      George, P. Sutton, & Oscar, Biblarz. (2017). Rocket Propulsion Elements, Ninth Edition, WILEY, Inc. All rights reserved.
[28]      Panayiota, A., & Silvio, B. (2023). Recent progress for hydrogen production from ammonia and hydrous hydrazine decomposition. Journal of Catalyst Today, 423(1) 114022.
[29]      Zhipeng Zhang, & Baole li. (2022). Catalytic decomposition of hydroxylamine nitrate and hydrazine nitrate using Ru/ZSM-5 catalyst under mild reaction conditions. Journal of RSC Advances, 12(8), 4469–4474.
[30]      Ilaria B., Silvio B., Simone T., & Patricia F. (2022). Selective decomposition of hydrazine over metal free carbonaceous materials. Journal of Phys. Chem. Phys., 24, 3017.
[31] Barbara Miranda Morales. (2017). Effect of preparation method on catalytic activity of Ni/ γ-Al2O3 catalysts. Journal of Ingenieria, 27 (1), 21-38
[32]      Sungsik, L., Chaoyang, F., Tianpin, W. & Scott, L. A. (2005). Hydrazine decomposition over Irn/Al2O3 model catalysts prepared by size-selected cluster deposition. Journal Phys. Chem., 109, 381-388.
[33]      Wucherer E. J., Timothy C. & Stiefel, M. (2013). Hydrazine catalyst production-sustaining S-405 technology NTRS, 39th Joint AIAA, Document ID 20030066232.