Robust autolanding system design for a combat aircraft on the ground

Within the scope of this thesis, a 6-degree-of-freedom model of a combat aircraft is created. Apart from the flight dynamics, landing gear dynamics on the ground are also modeled. After that, a robust autolanding system is designed for the autoland part after the main landing gears touch the ground until the aircraft stops. For the outer guidance loop line following guidance algorithms are compared and the linear sliding mode guidance algorithm is found to be the best in terms of the combination of line tracking and required control effort. For the inner autopilot loop sliding mode control (SMC) and proportional integral derivative (PID) control are used. Feedforward gains are also added for increased disturbance rejection. The designed autoland systems are tested against crosswind, brake failures, steering failure, and decreased cornering power factor for main landing gear tires. It has been found that SMC is as robust as PID control for inner loop applications.