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

Document Type: Research Article

Authors

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

2 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.

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