S. Račkauskas “Investigation of internal ballistics of solid propellant rocket motor by numerical and experimental methods” doctoral dissertation defence

Thesis Defense

Author, Institution: Saulius Račkauskas, Kaunas University of Technology

Science area, field of science: Technological Sciences, Mechanical Engineering, T009

Scientific Supervisor:
Prof. Dr. Habil. Algimantas Fedaravičius (Kaunas University of Technology, Technological Sciences, Mechanical Engineering, T009)

Dissertation Defence Board of Mechanical Engineering Science Field:
Prof. Dr. Rimvydas Gaidys (Kaunas University of Technology, Technological Sciences, Mechanical Engineering, T009) – chairman
Prof. Dr. Habil. Marijonas Bogdevičius (Vilnius Gediminas Technical University, Technological Sciences, Mechanical Engineering, T009),
Prof. Dr. Volodymyr Hutsaylyuk (Military University of Technology, Poland, Technological Sciences, Mechanical Engineering, T009),
Prof. Dr. Artūras Keršys (Kaunas University of Technology, Technological Sciences, Transport Engineering, T003).

For attendance of remote dissertation defence please join Zoom  meeting room.

The doctoral dissertation is available on the internet and at the library of Kaunas University of Technology (K. Donelaičio g. 20, Kaunas).

Annotation:

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.

Premium WordPress Themes Download
Download Premium WordPress Themes Free
Download WordPress Themes
Free Download WordPress Themes
free online course
We are using cookies to provide statistics that help us give you the best experience of our site. You can find out more or switch them off if you prefer. However, by continuing to use the site without changing settings, you are agreeing to our use of cookies.
I agree