Authors: Wei Zhang; Jing Min Dai; Guo You Zhang
Addresses: School of Electrical Engineering and Automation, Harbin Institute of Technology, Harbin 150001, China. ' School of Electrical Engineering and Automation, Harbin Institute of Technology, Harbin 150001, China. ' China Aerodynamics Research Institute of Aeronautics, Harbin 150001, China
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.
Keywords: 2kπ support mode; mathematical modelling; computer control; motion control; aircraft models; aircraft design; attitude simulation; aeroplane modelling; wind tunnel testing.
International Journal of Computer Applications in Technology, 2011 Vol.42 No.4, pp.321 - 324
Received: 08 May 2021
Accepted: 12 May 2021
Published online: 09 Mar 2012 *