Abstract:

The control redundancy is overcome with a “cosine” distribution method. The coupling between control channels is resolved with inner/outer loop control configuration. A unified model of the flight control system is realized for different flight modes. In the face of difficulty from modeling dynamics of tilt-rotor aircraft, pseudo partial derivative and pseudo order are introduced, and a model free adaptive flight control law is designed. The adaptability and robustness of the flight control system to the nonlinearity, time varying and uncertainty of controlled plant are improved. The control performance of adaptability and robustness are verified with simulation, in which the modelfree adaptive flight controller is superior to proportion integration differentiation (PID) controller. A simulation process is given out, in which the tilt-rotor aircraft emulates a flight process from helicopter mode, conversion mode to airplane mode. It is demonstrated that the model free adaptive control can be applied to the design of tilt-rotor aircraft flight control systems. A new control method is provided for the flight control system of the tilt-rotor aircraft, which is easy to engineering implementation.