Volume 37, Number 3, June 2019
|Page(s)||523 - 531|
|Published online||20 September 2019|
Design of Control Law of Post Stall Maneuver under Unsteady Aerodynamics Based on Improved Dynamic Inverse Method
School of Automation, Northwestern Polytechnical University, Xi’an, 710072, China
In this paper, a practical improved dynamic inverse control method is proposed to solve the large control error and control hysteresis of post stall maneuver under unsteady aerodynamics. Firstly, depending on the wind tunnel experimental data of the advanced fighter aircraft model under biaxial coupled large oscillation, an accurate unsteady aerodynamic model is established by using the improved extreme learning machine (ELM) method. Secondly, in terms of the time scale separation, the control error caused by unsteady aerodynamic is reduced by adding integral in the fast loop, and the control delay caused by unsteady aerodynamic is eliminated by applying the lag correction link in the slower loop. The deflections of conventional aerodynamic surface and thrust vector are allocated by the daisy chain method. Finally, the formula of the reduced frequency, which is the key factor in the unsteady aerodynamic modelling process, is derived by analyzing the wind tunnel data. The effectiveness of the present method for the scaled model is verified by herbst post stall maneuver. The present work provides a practical and reliable way for the flight test of post stall maneuver.
Key words: biaxial coupling oscillation / unsteady aerodynamics / improved ELM method / improved dynamic inverse method / herbst maneuver
关键字 : 双轴耦合振荡 / 非定常气动力 / 改进ELM / 改进动态逆 / 赫伯斯特机动
© 2019 Journal of Northwestern Polytechnical University. All rights reserved.
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