Specific Impulse and Ignition Delay Time Assessment for DMAZ with Liquid Oxidizers for an Upper Stage Rocket Engine

Document Type : Research Article

Authors

Faculty of Chemistry & Chemical Engineering, Malek Ashtar University of Technology, P.O. Box 11365-8486, Tehran, I.R. IRAN

Abstract

2-Dimethyl amino ethyl azide (DMAZ) has attracted much attention as a suitable liquid fuel replacement for monomethyl hydrazine (MMH) and unsymmetrical dimethyl hydrazine (UDMH) in propellant systems because, in contrast to these fuels, it is noncarcinogen. In this research, performance, and ignition delay time of DMAZ were studied with common liquid oxidizers such as inhibited red fuming nitric acid (IRFNA), dinitrogen tetroxide (N2O4), White Fuming Nitric Acid (WFNA). Calculation results from rocket propulsion analysis (RPA) software showed that combustion of DMAZ and N2O4yielded highest Isp (352 s) compared to the other mentioned oxidizers. Moreover, DMAZ-N2O4 gave the highest density specific impulse (457.6­ s) at an optimum oxidizer-to-fuel ratio. Open cup tests were also performed to assess the ignition behavior of the DMAZ-N2O4 bipropellant and indicated that it is hypergolic (68 ms). Therefore, it seems that
the DMAZ-N2O4 bipropellant is suitable for upper stage space systems.

Keywords

Main Subjects

References

1] Wang S., Thynell S.T., Chowdhury A., Experimental Study on Hypergolic Interaction Between N, N, N′, N′-Tetramethylethylenediamine and Nitric Acid, Energy Fuels, 24(10): 5320-5330 (2010).
[2] Pakdehi S.G., Rouhandeh H., Sub-Atmospheric Distillation for Water (1) + Dimethyl Amino Ethyl Azide (2) Mixture, Iran. J. Chem. Chem. Eng. (IJCCE), 35 (2): 107-111 (2016).
[3] Zhang P., Zhang L., Law C.K., Density Functional Theory Study of the Reactions of 2-Azido-N, N-Dimethylethanamine with Nitric Acid and Nitrogen Dioxide, Combust. Flame, 162(1): 237-248 (2015).
[4] Pakdehi S.G., Ajdari S., Hashemi A., Keshavarz M.H., Performance Evaluation of Liquid Fuel 2-Dimethyl Amino Ethyl Azide (DMAZ) with Liquid Oxidizers, J. Energ. Mater., 33(1): 17-23 (2015).
[5] Gordon S., McBride B.J., "Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications I. Analysis", Citeseer, Ohio (1996).
[6] Ponomarenko A., "Rocket Propulsion Analysis Software",2nd ed, Cologne, Germany (2012).
[7] Sutton G.P., Biblarz O., "Rocket Propulsion Elements", John Wiley & Sons, New York (2010).
[8] Wang S., Thynell S., Experimental Investigation of Pressure Effect on Ignition Delay of Monomethylhydrazine, 1, 1‐Dimethylhydrazine, Tetramethylethylenediamine and 2‐Dimethylaminoethylazide with Nitric Acid, "8th U.S. National Combustion Meeting", 1-6 (2013).
[9] Davis S.M., Yimaz N., Thermochemical Analysis of Hypergolic Propellants Based on Triethylaluminum/ Nitrous Oxide, Int. J. Aerosp. Eng., 2014: 1-5 (2014).
[10] Liu W.G., Dasgupta S., Zybin S.V., Goddard W.A., First Principles Study of the Ignition Mechanism for Hypergolic Bipropellants: N, N, N′, N′-Tetramethylethylenediamine (TMEDA) and N, N, N′, N′-Tetramethylmethylenediamine (TMMDA) with Nitric Acid, J. Phys. Chem. A, 115(20): 5221-5229 (2011).
[11] Pourpoint T.L., Anderson W.E., Hypergolic Reaction Mechanisms of Catalytically Promoted Fuels with Rocket Grade Hydrogen Peroxide, Combust. Sci. Technol., 179(10): 2107-2133 (2007).
[12] Hallit R.E.A, George B., Hypergolic Azide Fuels with Hydrogen Peroxide, US Patent 6949152 B2 (2005).
[13] Schneider S., Hawkins T., Ahmed Y., Deplazes S., Mills J., "Ionic Liquids: Science and Applications, Chapter1: Ionic Liquid Fuels for Chemical Propulsion", ACS Sympsium Series, New York (2012).
Iranian Journal of Chemistry and Chemical Engineering (IJCCE)
Volume 36, Issue 6 - Serial Number 86
November and December 2017
Pages 171-176

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