Recursive identification of nonlinear aerodynamic characteristics of air-plane

Abstract

The subject of the paper concerns the method of on-line identification, especially considering the formof equation of air-plane motion. The main idea is using the table representation of the function. The proposed approximation of the data obtained during the experiment is the basis of the recursive algorithm, which can find the best approximation in the area of excitation. The test results shows the importance of proper design of the stimulation signals. This signal should be sum of low-frequency set-point component and high-frequency part. For the purpose of presentation identification of the cm aerodynamic coefficient of an air-plane is presented.