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

Iuliia Zaitceva, Boris Andrievsky

Результат исследований: Научные публикации в периодических изданияхстатья в журнале по материалам конференциирецензирование

1 Цитирования (Scopus)

Аннотация

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.

Язык оригиналаанглийский
Номер статьи012055
ЖурналJournal of Physics: Conference Series
Том1864
Номер выпуска1
DOI
СостояниеОпубликовано - 20 мая 2021
Событие13th Multiconference on Control Problems, MCCP 2020 - Saint Petersburg, Российская Федерация
Продолжительность: 6 окт 20208 окт 2020

Предметные области Scopus

  • Физика и астрономия (все)

Fingerprint

Подробные сведения о темах исследования «Optimization of the manned aircraft pitch angle control loop with actuator rate limitation and nonlinear correction». Вместе они формируют уникальный семантический отпечаток (fingerprint).

Цитировать