The estimation of control systems stability boundaries by the describing function method by example of aircraft

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The estimation of control systems stability boundaries by the describing function method by example of aircraft. / Zaitceva, Iuliia; Chechurin, Leonid.

в: Cybernetics and Physics, Том 9, № 2, 30.09.2020, стр. 117-122.

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

BibTeX

@article{93f2e6b634d640b7a8471563c3e5af1e,

title = "The estimation of control systems stability boundaries by the describing function method by example of aircraft",

abstract = "In this paper, the conditions for periodic modes forma-tion in the closed-loop pilot-vehicle system in the compensatory control mode are established. The case of high gain pilot task is considered under the conditions of a sudden disturbance, as well as under the influence of the system nonlinearities, such as actuator position and rate limit. Sinusoidal input describing function method and parametric resonance equation were used to determine the onset conditions for self-oscillations and forced os-cillations. The case when this methods lead to erroneous results is established. The numerical limits of permissi-ble pilot gain, time delay and reference signal at which unstable periodic modes do not arise are calculated.",

keywords = "Aircraft, Describing function, Forced oscillations, Nonlinear, PIO, Self-oscillations, Time de-lay",

author = "Iuliia Zaitceva and Leonid Chechurin",

year = "2020",

month = sep,

day = "30",

language = "English",

volume = "9",

pages = "117--122",

journal = "Cybernetics and Physics",

issn = "2223-7038",

publisher = "IPACS",

number = "2",

}

RIS

TY - JOUR

T1 - The estimation of control systems stability boundaries by the describing function method by example of aircraft

AU - Zaitceva, Iuliia

AU - Chechurin, Leonid

PY - 2020/9/30

Y1 - 2020/9/30

N2 - In this paper, the conditions for periodic modes forma-tion in the closed-loop pilot-vehicle system in the compensatory control mode are established. The case of high gain pilot task is considered under the conditions of a sudden disturbance, as well as under the influence of the system nonlinearities, such as actuator position and rate limit. Sinusoidal input describing function method and parametric resonance equation were used to determine the onset conditions for self-oscillations and forced os-cillations. The case when this methods lead to erroneous results is established. The numerical limits of permissi-ble pilot gain, time delay and reference signal at which unstable periodic modes do not arise are calculated.

AB - In this paper, the conditions for periodic modes forma-tion in the closed-loop pilot-vehicle system in the compensatory control mode are established. The case of high gain pilot task is considered under the conditions of a sudden disturbance, as well as under the influence of the system nonlinearities, such as actuator position and rate limit. Sinusoidal input describing function method and parametric resonance equation were used to determine the onset conditions for self-oscillations and forced os-cillations. The case when this methods lead to erroneous results is established. The numerical limits of permissi-ble pilot gain, time delay and reference signal at which unstable periodic modes do not arise are calculated.

KW - Aircraft

KW - Describing function

KW - Forced oscillations

KW - Nonlinear

KW - PIO

KW - Self-oscillations

KW - Time de-lay

UR - http://www.scopus.com/inward/record.url?scp=85091839233&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:85091839233

VL - 9

SP - 117

EP - 122

JO - Cybernetics and Physics

JF - Cybernetics and Physics

SN - 2223-7038

IS - 2

ER -

ID: 86489182