THEORETICAL AND EXPERIMENTAL INVESTIGATIONS ON ROCKET PROPULSION OF COUNTERPROJECTILE OF ACTIVE PROTECTION SYSTEM

The paper presents selected results of a research project the aim of which is to perform the technology demonstrator of an active protection system. One of the elements of this system is a smart counterprojectile. The counterprojectile head includes electronic components sensitive to high overload. To avoid such overload effects, a solid propellant rocket engine was used as a propulsion system. The design concept of a propulsion system of a counterprojectile is described. Due to short operation time, it is assumed that the propellant system will have the features of a rocket booster. A propellant charge will consist of seven rocket propellant grains with low-combustible layer thickness and a large area of burning, ensuring high-power engine thrust. Based on the Polish new homogeneous solid rocket propellant, and adopted dimensions of the propellant charge and nozzle block, calculations of ballistic characteristics of the propulsion system were carried out. In order to verify the results of a theoretical analysis, experimental studies were carried out.