Abstract:

The linear optimal control theory is used for the optimal control law(elevator control, column angular displacement and throttle angular displacement) during landing that will enable an aircraft to get a safe landing and achieve the smallest possible longitudinal dispersion and sink rate deviation. Logarithmic windshear and downdraft were considered; airspeed profile, altitude, sink rate and attitude angle were tracked to improve the effects of windshear on flight. One aircraft has been simulated on IBM 4341.

Key words: Windshear, Automatic landing, Optimal control law.