Auto -landing Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLClanding Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLClanding Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLC landing Control System Design Using Combined ILS/FLClanding Contro

Airplane control during landing phase is important because it requires simultaneous control of several variables such as velocity, height and flight path angle, so, the purpose of this research is to access a desirable way to make this manoeuvre more convenient for pilots and improve its safety for passengers with using Instrument Landing system and Fuzzy Logic concept with respect to atmospheric turbulences and to find out the effects of longitudinal and vertical turbulence on the airplane stability. In this paper, in order to design Beaver DHC-2 airplane longitudinal control, classic control and fuzzy method in combination with ILS navigation system are used, and their main role is to approach and to adjust pitch angle rate in Glideslope and flare phases. PID controller lands the airplane with the help of ILS navigation system, from approach to flare, and the fuzzy controller helps the airplane to track the desired path during flare. One of the new control approaches that regardless of the plant complexity has successful result is fuzzy logic control. In this research fuzzy inference system beside PID approach was proposed to land aircraft on the desired path even if a harsh turbulence effects on it, so, this paper puts stress on the actual descending and touch down and flare phase of the landing in the presence of atmospheric turbulences.To illustrate the successful application of proposed control laws to the automatic control landing problem numerical simulations are carried out based on longitudinal nonlinear airplane model excited by the atmospheric turbulences. Simulation results are classified in two groups: airplane longitudinal parameters and stability with respect to the atmospheric turbulences. The first group appeals the successful results and appropriate stability for the nonlinear design. The second one also limits the airplane landing stability to an speed which make the landing process impossible. Design an automatic landing system that track the landing movements including glideslope and flare at the desired trajectory of Beaver DHC-2 aircraft which is derived from ILS equations using FLC in presence of atmospheric turbulence illustrates the innovation concept of this paper