Aircraft Turbojet Engine with Afterburning as Controlled Object

The paper deals with a turbojet engine with afterburning (TJEA) for aircraft use. Starting from basic engine's and afterburning's non-linear motion equations, the mathematical model was established. New form of model's equations were issued, by using the finite differences method to bring it to a linear form, brought to a dimensionless form after convenient equations’ processing and then the Laplace transformation was applied. TJEA's model was issued using the matrix description and their input and output parameters concerning the afterburning were identified. One has studied the variations of TJEA's essential coefficients (time constant and stability constant) in the range of afterburning's temperatures, but also depending on the flight altitude. Some aspects regarding TJEA's stability and quality (its time behavior) were also studied using its step response and some important conclusions drawn.