Design and Simulation Verification of Aircraft Altitude Control Based on Hybrid Algorithm

Abstract

In order to ensure the control quality and improve the maneuverability of the aircraft when completing some special missions, a hybrid algorithm for the altitude control loop was designed in this paper. The algorithm took the pitch angle as the inner loop of height control. When the height changed sharply, the speed propulsion was used as the control target. On the contrary, the height control was still used to ensure the stability of the control. Through simulation analysis and reasonable selection of threshold, the algorithm could effectively meet the control task. At the same time, the algorithm was applied to the experimental system. It is verified that the algorithm could quickly restore the aircraft to the target position and maintain better control quality when the height fluctuated greatly.