Control System of Quad-Rotor Aircraft Based on EDA

In recent years, estimation of distribution algorithms (EDA) has attracted widespread attention in the international academic community, making this algorithm as a popular tool widely used in the actual optimization of flight controllers. The flight control system is an important part of the aircraft design, and its control performance determines the performance of the aircraft to a large extent. The purpose of this paper is to study the quadrotor control system based on the EDA. This article introduces the working principle of the quad-rotor aircraft control system, improves the EDA structure, designs the quad-rotor aircraft control system, and finally conducts experiments on the aircraft control system. The experimental data shows that the maximum error between the actual measured altitude of the quadrotor and the expected hovering altitude value is 0.16 m, and the aircraft basically moves along the expected trajectory preset in the experiment. This shows that the system altitude has good control performance.