| Abstract [eng] |
The dissertation discusses the relevant case of the development of a unified construction methodology for solid-propellant rocket motors, based on numerical modelling of internal ballistics of the motor, evaluating the energy properties of the solid-propellant rocket motor and its geometrical parameters. For this purpose, a 3D geometric model of a solid-propellant rocket motor has been developed, in which the energy properties of the rocket propellant and the specifics of its combustion in the motor combustion chamber and nozzle discharge zone have been evaluated. The initial and boundary conditions of the model constrains the pressure and temperature parameters in the combustion chamber which has a direct effect on the physical properties of the fluid and solid domains, enabling to model the combustion process of a solid-propellant rocket motor with sufficient accuracy and to determine the internal ballistic characteristics of the motor. The comparative analysis was performed on theoretical and experimental results, the modelling results were verified while the motor was operating in steady-state. The practical application of the developed methodology reduces or completely eliminates the need for experimental testing, which allows to develop solid-propellant rocket motors saving time and development costs or to improve the performance of the existing motors. |
