Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Research › peer-review
Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model. / Andrievsky, Boris; Kudryashova, Elena V.; Kuznetsov, Nikolay V.; Kuznetsova, Olga A.; Mokaev, Timur N.; Tomashevich, Stanislav.
ICNPAA 2018 World Congress: 12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences. ed. / Seenith Sivasundaram. Vol. 2046 American Institute of Physics, 2018. 020005.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Research › peer-review
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TY - GEN
T1 - Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model
AU - Andrievsky, Boris
AU - Kudryashova, Elena V.
AU - Kuznetsov, Nikolay V.
AU - Kuznetsova, Olga A.
AU - Mokaev, Timur N.
AU - Tomashevich, Stanislav
PY - 2018/12/4
Y1 - 2018/12/4
N2 - Modern aircraft, operating in nonlinear flight regimes at high angle of attack often exhibit a limit cycle oscillation in the roll angle known as the "wing rock phenomenon." When the wing rock appears, the roll angle trajectory undergoes oscillations of growing amplitude and asymptotically converges to the stable limit cycle. The wing rock dynamics are represented by essentially nonlinear model, which parameters are varying in the wide range depending on the flight conditions (altitude, Mach number, mass of the payload, etc.) and the angle of attack. The promising approach of wing rock suppression and roll angle control under parametric uncertainty condition is an application of adaptation methods. In the paper, the simple adaptive control with the so-called "Implicit Reference Model" is applied for ensuring the smooth tracking the roll angle of the reference (desired) trajectory with wing rock suppression. The simulations are made for various angle of attack, showing the efficiency of the proposed method.
AB - Modern aircraft, operating in nonlinear flight regimes at high angle of attack often exhibit a limit cycle oscillation in the roll angle known as the "wing rock phenomenon." When the wing rock appears, the roll angle trajectory undergoes oscillations of growing amplitude and asymptotically converges to the stable limit cycle. The wing rock dynamics are represented by essentially nonlinear model, which parameters are varying in the wide range depending on the flight conditions (altitude, Mach number, mass of the payload, etc.) and the angle of attack. The promising approach of wing rock suppression and roll angle control under parametric uncertainty condition is an application of adaptation methods. In the paper, the simple adaptive control with the so-called "Implicit Reference Model" is applied for ensuring the smooth tracking the roll angle of the reference (desired) trajectory with wing rock suppression. The simulations are made for various angle of attack, showing the efficiency of the proposed method.
UR - http://www.scopus.com/inward/record.url?scp=85058685734&partnerID=8YFLogxK
U2 - 10.1063/1.5081525
DO - 10.1063/1.5081525
M3 - Conference contribution
AN - SCOPUS:85058685734
VL - 2046
BT - ICNPAA 2018 World Congress
A2 - Sivasundaram, Seenith
PB - American Institute of Physics
T2 - 12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences, ICNPAA 2018
Y2 - 3 July 2018 through 6 July 2018
ER -
ID: 38349831