A1 Alkuperäisartikkeli tieteellisessä aikakauslehdessä
Aircraft wing rock oscillations suppression by simple adaptive control (2020)

Andrievsky, B., Kudryashova, E. V., Kuznetsov, N. V., & Kuznetsova, O. A. (2020). Aircraft wing rock oscillations suppression by simple adaptive control. Aerospace Science and Technology, 105, Article 106049. https://doi.org/10.1016/j.ast.2020.106049

JYU-tekijät tai -toimittajat

Julkaisun tiedot

Julkaisun kaikki tekijät tai toimittajat: Andrievsky, Boris; Kudryashova, Elena V.; Kuznetsov, Nikolay V.; Kuznetsova, Olga A.

Lehti tai sarja: Aerospace Science and Technology

ISSN: 1270-9638

eISSN: 1626-3219

Julkaisuvuosi: 2020

Volyymi: 105

Artikkelinumero: 106049

Kustantaja: Elsevier

Julkaisumaa: Ranska

Julkaisun kieli: englanti

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

Julkaisun avoin saatavuus: Ei avoin

Julkaisukanavan avoin saatavuus: 

Tiivistelmä

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.

YSO-asiasanat: säätötekniikka; lentotekniikka; värähtelyt; matemaattiset mallit; säätöteoria

Vapaat asiasanat: nonlinear control; adaptive control; robustness; limit cycle oscillation; wing rock; aircraft; implicit reference model

Liittyvät organisaatiot

OKM-raportointi: Kyllä

Raportointivuosi: 2020

JUFO-taso: 1