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.

Original languageEnglish
Article number012055
JournalJournal of Physics: Conference Series
Volume1864
Issue number1
DOIs
StatePublished - 1 May 2021
Event13th Multiconference on Control Problems, MCCP 2020: Математическая теория управления и ее приложения (МТУиП) - ГНЦ РФ АО «Концерн «ЦНИИ «Электроприбор», Санкт-Петербург, Russian Federation
Duration: 6 Oct 20208 Oct 2020
Conference number: 13
http://www.elektropribor.spb.ru/nauchnaya-deyatelnost/xiii-mkpu/index3.php

    Scopus subject areas

  • Physics and Astronomy(all)

ID: 86489041