Linear mathematical model of single-spool micro turbojet engine with fixed exhaust nozzle

Main goal of this paper is to develop a linear state space representation of a micro turbojet engine based on physical laws describing the operation of the power plant. The importance of micro turbine engines is constantly rising; therefore it is essential to improve their reliability through advanced control systems. They can produce shaft power and heat in industrial applications and they can be used as propulsion for small scale manned or unmanned aerial vehicles as well. In either form of usage safety is a primary factor hence the development of suitable mathematical models to describe the behavior of the engine is essential. The present simplified model is focusing on such micro turbojets that have a thrust range of 100 to 2000N and include a fixed exhaust nozzle. The developed model is intended to be used in a linear quadratic control after future identification of the real gas turbine engine.