Developing a universal Software for the Conceptual Design of Cryogenic Rocket Propulsion System

In this article, a universal algorithm and engineering software is presented for the conceptual design of cryogenic rocket propulsion system. The algorithm consisting five engine working cycles: pressure fed, gas generator, staged combustion, closed and opened expansion cycles. For validation, the Vulcain and HM7B engines were redesigned, the obtained results certifies that the main design parameters have less than 5% errors and the other less than 20%. One of the advantages of this software is the presence of abut 150 parameters in the output and 14 diagrams related to the flow behavior in the thrust chamber and cooling vest, which allows the parametric study of the effect of input changes on the outputs. The modeling of mathematical functions and the combustion has been done, by using the MATLAB and CEA software. Finally, by merging in Visual studio programming environment and with the help of C# programming language, a software with GUI is presented.