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Markelov, G. N.;

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Development of computer model and preliminary design of the monopropellant (nitrous oxide) thruster that will be working under space vacuum conditions are presented in this paper. To perform such a design, two models have been developed, plug flow reactor and lumped thruster models. The plug flow reactor has been used to study conditions under which a thermal decomposition of nitrous oxide occurs. A range of initial temperature and pressure has been found that is used as initial guess for the thruster design. To perform a preliminary design of the thruster, the lumped model has been used. The model takes into account gas flow through the thruster, propellant decomposition, and heat exchange between thruster elements and gas and it is based on Zakirov’s model. The novelty is that the current model does not need experimental data on combustion pressure as input parameter. The model has been applied to find a suitable design, for example, thruster size and working pressure for a given power range. Calculated time to achieve a steady state firing is in good agreement with available information on manufactured thrusters.

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Palavras-chave: nitrous oxide, plug flow reactor, lumped thruster mode, low power.,


DOI: 10.5151/meceng-wccm2012-15646

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Como citar:

Markelov, G. N.; "COMPUTER DESIGN OF LOW POWER N2O MONOPROPELLANT THRUSTER", p. 19-29 . In: In Proceedings of the 10th World Congress on Computational Mechanics [= Blucher Mechanical Engineering Proceedings, v. 1, n. 1]. São Paulo: Blucher, 2014.
ISSN 2358-0828, DOI 10.5151/meceng-wccm2012-15646

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