Modelling, simulation and optimal control for an aircraft of aileron-lessfolding wing

摘要

The purpose of this paper is to discuss the method of modeling and controlsystem design for a loitering aircraft of aileron-less folding wing. A nonlinearmodel of the aircraft was established, and then linearized by small disturbancemethod. The lateral-directional stability augmentation options were analyzedthrough the root locus plots. The pole placement method based on linearquadratic regulator (LQR) technology was used to achieve desirable dynamiccharacteristics. In the analysis, the state parameters which represent rapidoscillation states of the aircraft such as roll rate and yaw rate were set asprimary control parameters in the inner loop. The states oscillated slowly suchas rolling angle and yaw angle were set as main control parameters in the outerloop. Based on the self-organizing fuzzy control algorithm, the aircraft can becontrolled to fly in a desired path. Two types of course control plan wereinvestigated and verified. The results show that the control plans are feasibleand the control system is adequately robust to meet the requirements of thecourse control.