**3. Flight dynamics and control**

The flight dynamics mathematical model of an aircraft, which would be strictly determined, would comprise of a system of non-linear, non-stationary, partial differential equations. To simplify these equations we introduce a number of assumptions. Ignored are the elastic characteristics of the aircraft so the aircraft can be thought as a rigid body and, in that way, the dispersal of parameters is eliminated. Also, fuel consumption is disregarded and so the non-stationarity due to temporal change in helicopter mass is eliminated.
