Синтез нелинейных корректирующих звеньев для предотвращения колебаний пилотируемых летательных аппаратов

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Синтез нелинейных корректирующих звеньев для предотвращения колебаний пилотируемых летательных аппаратов. / Zaitceva, Iuliia S.

в: Differencialnie Uravnenia i Protsesy Upravlenia, Том 2021, № 2, 2021, стр. 101-125.

Результаты исследований: Научные публикации в периодических изданиях › статья › Рецензирование

BibTeX

@article{c117006a4f5b40ceb00486dbe61104b1,

title = "Синтез нелинейных корректирующих звеньев для предотвращения колебаний пилотируемых летательных аппаратов",

abstract = "It is known from engineering practice that the actuators of the aircraft control surfaces have physical limits of thrust which are manifested in the nonlinear effects of actuator rate and the level saturation. In turn, the influence of nonlinearities causes a negative phase shift between the actual and control pilot signal, which negatively affects the stability of the aircraft. As a result, nonlinear oscillations of the aircraft's angular motion may arise, which endanger flight safety. To prevent fluctuations various methods have been developed, but there is no general approach to modeling. In this paper, the nonlinear correcting device synthesis methods is proposed. It is illustrated by the example of stabilizing the pitch angle in a piloted aircraft control system. The synthesis is implemented on the base of the optimization of system parameters and uses the Matlab/Simulink dynamic modeling software package. As a result of the study, the algorithm for the synthesis of a nonlinear correcting device is presented on the example of a remotely controlled UAV. The parameters of the pilot model, at which pilot-induced oscillations occur, are obtained. The properties of the optimal system are illustrated and evaluated using frequency response, pitch transients, and flight characteristics.",

keywords = "Airplane, Frequency method, Lag, Nonlinear correction, Optimization, Oscillation avoidance, Phase shift, Pilot model, Sensitivity function",

author = "Zaitceva, {Iuliia S.}",

year = "2021",

language = "русский",

volume = "2021",

pages = "101--125",

journal = "ДИФФЕРЕНЦИАЛЬНЫЕ УРАВНЕНИЯ И ПРОЦЕССЫ УПРАВЛЕНИЯ",

issn = "1817-2172",

publisher = "Электронный журнал {"}Дифференциальные уравнения и процессы управления{"}",

number = "2",

}

RIS

TY - JOUR

T1 - Синтез нелинейных корректирующих звеньев для предотвращения колебаний пилотируемых летательных аппаратов

AU - Zaitceva, Iuliia S.

PY - 2021

Y1 - 2021

N2 - It is known from engineering practice that the actuators of the aircraft control surfaces have physical limits of thrust which are manifested in the nonlinear effects of actuator rate and the level saturation. In turn, the influence of nonlinearities causes a negative phase shift between the actual and control pilot signal, which negatively affects the stability of the aircraft. As a result, nonlinear oscillations of the aircraft's angular motion may arise, which endanger flight safety. To prevent fluctuations various methods have been developed, but there is no general approach to modeling. In this paper, the nonlinear correcting device synthesis methods is proposed. It is illustrated by the example of stabilizing the pitch angle in a piloted aircraft control system. The synthesis is implemented on the base of the optimization of system parameters and uses the Matlab/Simulink dynamic modeling software package. As a result of the study, the algorithm for the synthesis of a nonlinear correcting device is presented on the example of a remotely controlled UAV. The parameters of the pilot model, at which pilot-induced oscillations occur, are obtained. The properties of the optimal system are illustrated and evaluated using frequency response, pitch transients, and flight characteristics.

AB - It is known from engineering practice that the actuators of the aircraft control surfaces have physical limits of thrust which are manifested in the nonlinear effects of actuator rate and the level saturation. In turn, the influence of nonlinearities causes a negative phase shift between the actual and control pilot signal, which negatively affects the stability of the aircraft. As a result, nonlinear oscillations of the aircraft's angular motion may arise, which endanger flight safety. To prevent fluctuations various methods have been developed, but there is no general approach to modeling. In this paper, the nonlinear correcting device synthesis methods is proposed. It is illustrated by the example of stabilizing the pitch angle in a piloted aircraft control system. The synthesis is implemented on the base of the optimization of system parameters and uses the Matlab/Simulink dynamic modeling software package. As a result of the study, the algorithm for the synthesis of a nonlinear correcting device is presented on the example of a remotely controlled UAV. The parameters of the pilot model, at which pilot-induced oscillations occur, are obtained. The properties of the optimal system are illustrated and evaluated using frequency response, pitch transients, and flight characteristics.

KW - Airplane

KW - Frequency method

KW - Lag

KW - Nonlinear correction

KW - Optimization

KW - Oscillation avoidance

KW - Phase shift

KW - Pilot model

KW - Sensitivity function

UR - http://www.scopus.com/inward/record.url?scp=85114104951&partnerID=8YFLogxK

M3 - статья

AN - SCOPUS:85114104951

VL - 2021

SP - 101

EP - 125

JO - ДИФФЕРЕНЦИАЛЬНЫЕ УРАВНЕНИЯ И ПРОЦЕССЫ УПРАВЛЕНИЯ

JF - ДИФФЕРЕНЦИАЛЬНЫЕ УРАВНЕНИЯ И ПРОЦЕССЫ УПРАВЛЕНИЯ

SN - 1817-2172

IS - 2

ER -

ID: 86488989