The thermodynamic model of a solid-fuel rocket engine taking into account heat loss

The article’s study focuses on a technique to analyze the operational properties of solid-fuel rocket engines, specifically considering the heat dissipation through the combustion chamber wall. The mathematical model is derived from the concept of energy conservation to establish a problem model that closely resembles the real model. In addition, empirical research is undertaken to validate the theoretical concept. The computed outcomes are juxtaposed with the empirical outcomes to ascertain the dependability of the mathematical model. The C5K solid-fuel rocket engine was chosen for the purpose of computation and experimentation. The comparison between the theoretical calculation results and the experimental findings demonstrates a high degree of similarity between the model simulation results and the experimental data. The largest discrepancy between the theoretical calculation results and the actual results is 8.3%, which is within the acceptable threshold of less than 10%. The study’s results are used to evaluate the performance characteristics of solid-fuel rocket engines. This theoretical foundation is reliable and may serve as a blueprint for designers as they create, assemble, and enhance the entire framework of a solid-fuel rocket engine.