Thrust vectoring nozzle for small turbojet engine in laboratory conditions

The article deals with description of thermodynamic processes in a class of small turbojet engines with description of experimental and analytic modeling approaches to create a mathematical model. The model will describe a small turbojet engine as a system with one degree of freedom (fast exhaust nozzle), two degrees of freedom controlled by fuel supply and exhaust nozzle diameter. The article then deals with extension of such model with the third degree of freedom in the form of thrust vector. Such system developed for a small turbojet engine can be beneficial in applications with highly maneuverable small unmanned aerial vehicles.