Modelling and motion control for 2kπ support mode of aircraft model

Abstract

Wind tunnel test is an essential step in aircraft design and research. But simulation capabilities of present wind tunnels cannot satisfy the need of development on new aircrafts. To realise the attitude simulation of aircraft model, this study presents a set of support mechanism with 2kπ model. A mathematical model is established by coordinate conversion in which each attitude angle of aeroplane model is represented by a trigonometric function. In wind tunnel test, nine angle sections are adopted to realise the attitude control with large angle. The control strategy of 2kπ support mode is proved to be accurate enough.