Design and Experiment of Aircraft Transient Performance Attitude Control System

This paper is aimed at designing controllers for the aircraft attitude system possessing nonlinearity, coupling and unknown disturbance. A method for improvement based on adaptive performance functions is proposed from the traditional non-approximation prescribed performance control method. With the proposed method, the possible singular problem that might occur in the logarithmic functions that are adopted in the calculation of transformation error can be avoided in the design. The improved performance function can broaden the boundary when the error is out of bounds to ensure the coverage of the tracking error. The effectiveness and the correctness of the proposed method is verified using experiments of numerical and semi-physical simulation. And the experimental results show that the normal operation of the system can be safeguarded by the proposed method when the error is out of bounds. Finally, satisfactory control effects are achieved.