Determination of the working ratio of fuel components “AT + UDMH” in the combustion chamber

The object of the study is the fuel pair “nitrogen tetroxide and unsymmetrical dimethylhydrazine” and the ratio in which these components are supplied to the combustion chamber of a rocket engine. The purpose of the work is to calculate the working ratio of fuel components for the fuel pair under study. In the process of work, studies were carried out for the selected fuel pair, calculations in the Termoras program, construction and analysis of the obtained dependencies. As a result of work using the example of the RD-119 engine, the working ratio of fuel components was obtained and, according to the calculated ratio, engine parameters were determined, which can later be used to calculate propulsion system components.