Development of a Control Augmentation System for a Tilt-Rotor Aircraft

This thesis focus on a control augmentation system development for XV-15 Tilt-Rotor Aircraft. The main control actions are holding pitch, roll, together with a turn hold. These features are relevant for autonomous navigation and guidance purposes, in order to satisfy the mission requirements. Proportional-Integral-Derivative (PID) is one of the traditional control algorithms and plays key role in the achievement of given requirements. LEAD-LAG compensators features are cheked. The project is implemented on the simulator, in order to test the system and assess the handling qualities.