Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model

Результат исследований: Публикации в книгах, отчётах, сборниках, трудах конференцийстатья в сборнике материалов конференциинаучнаярецензирование

2 Цитирования (Scopus)

Выдержка

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.

Язык оригиналаанглийский
Название основной публикацииICNPAA 2018 World Congress
Подзаголовок основной публикации12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences
РедакторыSeenith Sivasundaram
ИздательAmerican Institute of Physics
Том2046
ISBN (электронное издание)9780735417724
DOI
СостояниеОпубликовано - 4 дек 2018
Событие12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences, ICNPAA 2018 - Yerevan, Армения
Продолжительность: 3 июл 20186 июл 2018

Конференция

Конференция12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences, ICNPAA 2018
СтранаАрмения
ГородYerevan
Период3/07/186/07/18

Отпечаток

wing rock
adaptive control
retarding
angle of attack
oscillations
trajectories
flight conditions
cycles
payloads
Mach number
aircraft
flight

Предметные области Scopus

  • Физика и астрономия (все)

Цитировать

Andrievsky, B., Kudryashova, E. V., Kuznetsov, N. V., Kuznetsova, O. A., Mokaev, T. N., & Tomashevich, S. (2018). Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model. В S. Sivasundaram (Ред.), ICNPAA 2018 World Congress: 12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences (Том 2046). [020005] American Institute of Physics. https://doi.org/10.1063/1.5081525
Andrievsky, Boris ; Kudryashova, Elena V. ; Kuznetsov, Nikolay V. ; Kuznetsova, Olga A. ; Mokaev, Timur N. ; Tomashevich, Stanislav. / Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model. ICNPAA 2018 World Congress: 12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences. редактор / Seenith Sivasundaram. Том 2046 American Institute of Physics, 2018.
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title = "Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model",
abstract = "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.",
author = "Boris Andrievsky and Kudryashova, {Elena V.} and Kuznetsov, {Nikolay V.} and Kuznetsova, {Olga A.} and Mokaev, {Timur N.} and Stanislav Tomashevich",
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Andrievsky, B, Kudryashova, EV, Kuznetsov, NV, Kuznetsova, OA, Mokaev, TN & Tomashevich, S 2018, Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model. в S Sivasundaram (ред.), ICNPAA 2018 World Congress: 12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences. том. 2046, 020005, American Institute of Physics, Yerevan, Армения, 3/07/18. https://doi.org/10.1063/1.5081525

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. ред. / Seenith Sivasundaram. Том 2046 American Institute of Physics, 2018. 020005.

Результат исследований: Публикации в книгах, отчётах, сборниках, трудах конференцийстатья в сборнике материалов конференциинаучнаярецензирование

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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.

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Andrievsky B, Kudryashova EV, Kuznetsov NV, Kuznetsova OA, Mokaev TN, Tomashevich S. Suppression of nonlinear wing-rock oscillations by adaptive control with the implicit reference model. В Sivasundaram S, редактор, ICNPAA 2018 World Congress: 12th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences. Том 2046. American Institute of Physics. 2018. 020005 https://doi.org/10.1063/1.5081525