STUDYING THE INFLUENCE OF THE NOZZLE PROFILE ON THE WORKING PERFORMANCE OF A SOLID-FUEL ROCKET ENGINE

Abstract

In this paper, a method to determine the typical working parameters of a
solid-fuel rocket engine taking into account some types of nozzle profiles are
established. A mathematical model describing the thermodynamic process of a
solid-fuel rocket engine is established based on thermodynamic and aerodynamic
relationships. The model has been calculated for the cruise engine of the 9K38
anti-aircraft guided missile (Russian). Based on the results, the paper evaluated
the influence of the nozzle profile on the performance of solid-fuel rocket engines.
The research results are an important theoretical basis for the process of designing
and selecting the optimal nozzle profile to minimize energy losses and improve
the working efficiency of the engine.