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Ghanbari Pakdehi, S., Shirzadi, B. (2017). Specific Impulse and Ignition Delay Time Assessment for DMAZ with Liquid Oxidizers for an Upper Stage Rocket Engine. Iranian Journal of Chemistry and Chemical Engineering (IJCCE), 36(6), 171-176.
Shahram Ghanbari Pakdehi; Bahman Shirzadi. "Specific Impulse and Ignition Delay Time Assessment for DMAZ with Liquid Oxidizers for an Upper Stage Rocket Engine". Iranian Journal of Chemistry and Chemical Engineering (IJCCE), 36, 6, 2017, 171-176.
Ghanbari Pakdehi, S., Shirzadi, B. (2017). 'Specific Impulse and Ignition Delay Time Assessment for DMAZ with Liquid Oxidizers for an Upper Stage Rocket Engine', Iranian Journal of Chemistry and Chemical Engineering (IJCCE), 36(6), pp. 171-176.
Ghanbari Pakdehi, S., Shirzadi, B. Specific Impulse and Ignition Delay Time Assessment for DMAZ with Liquid Oxidizers for an Upper Stage Rocket Engine. Iranian Journal of Chemistry and Chemical Engineering (IJCCE), 2017; 36(6): 171-176.

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

Article 17, Volume 36, Issue 6 - Serial Number 86, November and December 2017, Page 171-176  XML PDF (513.54 K)
Document Type: Research Article
Authors
Shahram Ghanbari Pakdehi email 1; Bahman Shirzadi2
1Faculty of Chemistry & Chemical Engineering, Malek Ashtar University of Technology, P.O. Box 11365-8486, Tehran, I.R. IRAN
2Faculty 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
DMAZ; Liquid oxidizers; Density specific impulse; Upper stage; Ignition delay time
Main Subjects
Applied Chemistry
References
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