TY - JOUR

T1 - Aircraft wing rock oscillations suppression by simple adaptive control

AU - Andrievsky, Boris

AU - Kudryashova, Elena V.

AU - Kuznetsov, Nikolay V.

AU - Kuznetsova, Olga A.

PY - 2020/10

Y1 - 2020/10

N2 - 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.

AB - 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.

KW - Adaptive control

KW - Aircraft

KW - Implicit reference model

KW - Limit cycle oscillation

KW - Nonlinear control

KW - Robustness

KW - Wing rock

KW - PASSIFICATION

KW - ROBUST

KW - SYSTEMS

KW - ATTITUDE-CONTROL

UR - http://www.scopus.com/inward/record.url?scp=85087589017&partnerID=8YFLogxK

UR - https://www.mendeley.com/catalogue/4889be0b-b81d-3806-8f40-7755fc91a19d/

U2 - 10.1016/j.ast.2020.106049

DO - 10.1016/j.ast.2020.106049

M3 - Article

AN - SCOPUS:85087589017

VL - 105

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

SN - 1270-9638

M1 - 106049

ER -