Standard

Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction. / Zaitceva, Iuliia; Andrievsky, Boris.

в: Journal of Physics: Conference Series, Том 1864, № 1, 012055, 01.05.2021.

Результаты исследований: Научные публикации в периодических изданиях › статья в журнале по материалам конференции › Рецензирование

Harvard

Zaitceva, I & Andrievsky, B 2021, 'Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction', Journal of Physics: Conference Series, Том. 1864, № 1, 012055. https://doi.org/10.1088/1742-6596/1864/1/012055

APA

Zaitceva, I., & Andrievsky, B. (2021). Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction. Journal of Physics: Conference Series, 1864(1), [012055]. https://doi.org/10.1088/1742-6596/1864/1/012055

Vancouver

Zaitceva I, Andrievsky B. Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction. Journal of Physics: Conference Series. 2021 Май 1;1864(1). 012055. https://doi.org/10.1088/1742-6596/1864/1/012055

Author

Zaitceva, Iuliia ; Andrievsky, Boris. / Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction. в: Journal of Physics: Conference Series. 2021 ; Том 1864, № 1.

BibTeX

@article{901a405de5dd4891bc60b5e458e1e845,
title = "Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction",
abstract = "In the paper a flight control system for a piloted aircraft on the pitch angle is considered, taking into account the rate saturation of the aircraft controlling surface. To prevent occurrence of the non-linear pilot-involved oscillations (PIO), a nonlinear correcting device is introduced into the control loop. On the basis of the pilot's adaptation to control tasks variations, his/her mathematical model parameters are optimized and the choice of the nonlinear correcting device parameters is proposed. The sensitivity functions of the non-linear system are calculated for harmonic and square-wave reference signals. The results of the optimized system simulations are presented demonstrating good performance of the closed-loop system with nonlinear correction.",
author = "Iuliia Zaitceva and Boris Andrievsky",
note = "Publisher Copyright: {\textcopyright} Published under licence by IOP Publishing Ltd.; 13th Multiconference on Control Problems, MCCP 2020 ; Conference date: 06-10-2020 Through 08-10-2020",
year = "2021",
month = may,
day = "1",
doi = "10.1088/1742-6596/1864/1/012055",
language = "English",
volume = "1864",
journal = "Journal of Physics: Conference Series",
issn = "1742-6588",
publisher = "IOP Publishing Ltd.",
number = "1",
url = "http://www.elektropribor.spb.ru/nauchnaya-deyatelnost/xiii-mkpu/index3.php",

}

RIS

TY - JOUR

T1 - Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction

AU - Zaitceva, Iuliia

AU - Andrievsky, Boris

N1 - Conference code: 13

PY - 2021/5/1

Y1 - 2021/5/1

N2 - In the paper a flight control system for a piloted aircraft on the pitch angle is considered, taking into account the rate saturation of the aircraft controlling surface. To prevent occurrence of the non-linear pilot-involved oscillations (PIO), a nonlinear correcting device is introduced into the control loop. On the basis of the pilot's adaptation to control tasks variations, his/her mathematical model parameters are optimized and the choice of the nonlinear correcting device parameters is proposed. The sensitivity functions of the non-linear system are calculated for harmonic and square-wave reference signals. The results of the optimized system simulations are presented demonstrating good performance of the closed-loop system with nonlinear correction.

AB - In the paper a flight control system for a piloted aircraft on the pitch angle is considered, taking into account the rate saturation of the aircraft controlling surface. To prevent occurrence of the non-linear pilot-involved oscillations (PIO), a nonlinear correcting device is introduced into the control loop. On the basis of the pilot's adaptation to control tasks variations, his/her mathematical model parameters are optimized and the choice of the nonlinear correcting device parameters is proposed. The sensitivity functions of the non-linear system are calculated for harmonic and square-wave reference signals. The results of the optimized system simulations are presented demonstrating good performance of the closed-loop system with nonlinear correction.

UR - http://www.scopus.com/inward/record.url?scp=85107429413&partnerID=8YFLogxK

U2 - 10.1088/1742-6596/1864/1/012055

DO - 10.1088/1742-6596/1864/1/012055

M3 - Conference article

AN - SCOPUS:85107429413

VL - 1864

JO - Journal of Physics: Conference Series

JF - Journal of Physics: Conference Series

SN - 1742-6588

IS - 1

M1 - 012055

T2 - 13th Multiconference on Control Problems, MCCP 2020

Y2 - 6 October 2020 through 8 October 2020

ER -

ID: 86489041