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

Document Type : Research Article


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


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.


Main Subjects

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).
[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).
[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).
[9] Davis S.M., Yimaz N., Thermochemical Analysis of Hypergolic Propellants Based on Triethylaluminum/ Nitrous Oxide, Int. J. Aerosp. Eng., 2014: 1-5 (2014).
[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).