Abstract
Nonlinear control using feedback linearization method is employed to develop automatic landing controller for a fighter aircraft. The three-degree-of-freedom nonlinear aircraft model with elevator as control input is established using the appropriate aerodynamic data from wind tunnel test. The model also considers the landing gears, flaps and speed brakes. Elevator is used to control the angle of attack by means of pitch attitude and throttle controls the speed. The feedback linearization control technique guarantees good tracking performance with respect to a given glideslope trajectory. An exponential trajectory is employed during the flare, which needs a tighter control and hence requires both the altitude and sink rate for the feedback purpose. The elevator dynamics and the engine dynamics are modelled for the simulation purpose. The controllers are tuned considering the “ground effect” encountered during landing, which was mathematically modelled. Nonlinear simulation under measurement noises and external disturbances are included in this study. Simulation results show the importance of designing the controller considering the ground effect.
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