Research output: Contribution to journal › Article › peer-review
Aircraft wing rock oscillations suppression by simple adaptive control. / Andrievsky, Boris; Kudryashova, Elena V.; Kuznetsov, Nikolay V.; Kuznetsova, Olga A.
In: Aerospace Science and Technology, Vol. 105, 106049, 10.2020.Research output: Contribution to journal › Article › peer-review
}
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 -
ID: 61326087