A1 Journal article (refereed)
Aircraft wing rock oscillations suppression by simple adaptive control (2020)


Andrievsky, Boris; Kudryashova, Elena V.; Kuznetsov, Nikolay V.; Kuznetsova, Olga A. (2020). Aircraft wing rock oscillations suppression by simple adaptive control. Aerospace Science and Technology, 105, 106049. DOI: 10.1016/j.ast.2020.106049


JYU authors or editors


Publication details

All authors or editors: Andrievsky, Boris; Kudryashova, Elena V.; Kuznetsov, Nikolay V.; Kuznetsova, Olga A.

Journal or series: Aerospace Science and Technology

ISSN: 1270-9638

eISSN: 1626-3219

Publication year: 2020

Volume: 105

Article number: 106049

Publisher: Elsevier

Publication country: France

Publication language: English

DOI: http://doi.org/10.1016/j.ast.2020.106049

Open Access: Publication channel is not openly available


Abstract

Roll angular motion of the modern aircraft operating in non-linear flight modes with a high angle of attack often demonstrates the limit cycle oscillations, which is commonly known as the wing rock phenomenon. Wing rock dynamics are represented by a substantially non-linear model, with parameters varying over a wide range, depending on the flight conditions (altitude, Mach number, payload mass, etc.) and angle of attack. A perspective approach of the wing rock suppression lies in the adaptation methods. In the present paper an application of the simple adaptive control approach with the Implicit Reference Model (IRM) is proposed and numerically studied. The IRM adaptive controller is applied to ensure smooth tracking the roll angle of the reference (desired) trajectory with the simultaneous wing rock prevention. As compared with the previous authors' work, in the present paper more complex and realistic model is employed, where interdependence between aircraft roll and sideslip motions and the limitations on the aileron deflection angle are explicitly taken into account at the stage of the controller design. To this aim, the modification of the IRM control scheme is suggested and numerically studied. The simulation results obtained demonstrate high efficiency of the proposed method.


Keywords: control engineering; aviation technology; oscillations; mathematical models; control theory

Free keywords: nonlinear control; adaptive control; robustness; limit cycle oscillation; wing rock; aircraft; implicit reference model


Contributing organizations


Ministry reporting: Yes


Last updated on 2020-17-07 at 14:14