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Numerical Study of Chemical Reaction for Liquid Rocket Propellant Using Equilibrium Constant
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 Title & Authors
Numerical Study of Chemical Reaction for Liquid Rocket Propellant Using Equilibrium Constant
Jang, Yo Han; Lee, Kyun Ho;
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Liquid rocket propulsion is a system that produces required thrust for satellites and space launch vehicles by using chemical reactions of a liquid fuel and a liquid oxidizer. Monomethylhydrazine/dinitrogen tetroxide, liquid hydrogen/liquid oxygen and RP-1/liquid oxygen are typical combinations of liquid propellants commonly used for the liquid rocket propulsion system. The objective of the present study is to investigate useful design and performance data of liquid rocket engine by conducting a numerical analysis of thermochemical reactions of liquid rocket propellants. For this, final products and chemical compositions of three liquid propellant combinations are calculated using equilibrium constants of major elementary equilibrium reactions when reactants remain in chemical equilibrium state after combustion process. In addition, flame temperature and specific impulse are estimated.
Liquid Rocket Propellant;Chemical Equilibrium;Equilibrium Constant;Adiabatic Flame Temperature;Specific Impulse;Monomethylhydrazine;Dinitrogen Tetroxide;
 Cited by
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