The design, research and practical application of rocket technology is a high-tech activity and is one of the hallmarks of any country’s scientific and industrial development.
The aim of the research project was to develop the theoretical and engineering design basis for an experimental rocket as a system with predefined internal and external ballistic parameters for scientific and defence purposes using an original eco-friendly rocket propellant, to carry out theoretical and experimental studies, and to practically develop an experimental mock-up of a rocket that is capable of delivering a payload (e.g. scientific equipment) to the required range.
Project funding:
Projects funded by the Research Council of Lithuania (RCL), Projects carried out by researchers’ teams
Project results:
The first stage involved the development of the engineering concept of the experimental rocket that may be used for short- and medium-range air defence system targets and research purposes, the key technical specifications, and the development of the research programme. The aerodynamic airflow study also resulted in the determination of aerodynamic drag force and coefficient dependencies on flight velocity which must be considered in the external ballistics studies of the rocket. The investigation of the strength of the rocket body and stabilising fins under aerodynamic loads was performed. A model of the chemical kinetics of the propellant is developed, giving values for temperature, pressure, enthalpy, entropy, gas constant and other parameters in the combustion chamber and exhaust nozzle of the engine. A theoretical model of the solid-propellant rocket motor was presented. The model is based on the laws of fluid dynamics and thermodynamics, the Navier-Stokes equations of fluid motion, the equations of heat transfer from the combustion chamber and nozzle, the equations of solid-fluid interaction during combustion, and the equations of combustion velocity and energy release. The motor design and manufacturing works were performed and the characteristics of pressure inside the motor combustion chamber and thrust were investigated.
A dual-purpose experimental rocket was designed and manufactured as a result of the investigations conducted. It may be used for research purposes, i.e. testing of nano- and pico-satellites, and other research equipment and airborne equipment (dynamic overload, temperature, pressure testing, etc.) and collection of data for research, and as the target for NASAMS medium-range air defence system exercise as well as other purposes in the area of defence technologies.
The research conducted expands the theoretical base of the rocket training equipment, and the designed and practically implemented equipment contributes to the strengthening of the air defence capabilities of Lithuania and NATO partners.
Period of project implementation: 2017-09-01 - 2020-09-30
Project coordinator: Kaunas University of Technology
