INTERNAL BALLISTICS CALCULATIONS OF THE SOLID PROPELLANT ROCKET ENGINE WITH TWO COMBUSTION CHAMBERS

Abstract

The paper presents the theoretical modeling of the internal ballistics properties of the solid propellant rocket engine with two combustion chambers. From the working characteristics of the solid propellant rocket engine with two combustion chambers and the theory of a solid propellant rocket engine, a system of equations that describes the processes that occur in the combustion chambers of the engine is established. Provide a method to solve the system of equations and necessary boundary conditions. Solve problems on model engines and verify theoretical results by experimental studies. The error between experimental studies and theoretical calculation is relatively small (less than 10%), confirming the reliability of the built mathematical model. Research results serve the design calculation and manufacture of the solid propellant rocket engine with two combustion chambers.