Lateral-Directional Attitude Controller Design on Fully Actuated System Method and Interference Compensation

With the research background of lateral-directional coupling and parameter disturbance issues in the aircraft, this paper derives the lateral-directional coupled small-perturbation linearized model of the aircraft and designs an interference compensation controller on the fully actuated system method. By combining the fully actuated system method with the active disturbance rejection control method, effective attitude control has been achieved. Through a comparative study of the control effects with the traditional PD method, it is demonstrated that the interference compensation controller on the fully actuated system method can still maintain precise control performance under parameter disturbances of the aircraft model, exhibiting the stability and robustness of this method.