bibtype	J - Journal Article
ARLID	0476150
utime	20240111140942.7
mtime	20170714235959.9
SCOPUS	85024485443
WOS	000405681300001
DOI	10.1049/iet-cta.2016.1067
title (primary) (eng)	On the internal stability of non-linear dynamic inversion: application to flight control
specification	page_count 13 s. media_type P
serial	ARLID cav_un_epca*0320539 ISSN 1751-8644 title IET Control Theory and Applications volume_id 11 volume 12 (2017) page_num 1849-1861
keyword	flight control
keyword	non-linear dynamic inversion
keyword	stability
author (primary)	ARLID cav_un_auth*0347646 name1 Alam name2 M. country CZ
author	ARLID cav_un_auth*0101074 name1 Čelikovský name2 Sergej full_dept (cz) Teorie řízení full_dept Department of Control Theory department (cz) TŘ department TR institution UTIA-B full_dept Department of Control Theory fullinstit Ústav teorie informace a automatizace AV ČR, v. v. i.
source	source_type článek url http://library.utia.cas.cz/separaty/2017/TR/celikovsky-0476150.pdf source_size 4.38 MB
cas_special	project ARLID cav_un_auth*0347203 project_id GA17-04682S agency GA ČR country CZ abstract (eng) Aircraft are highly non-linear systems, but flight control laws are traditionally designed from a set of linearised models. Due to the application of linear control laws on a non-linear system, the real performance ability of the aircraft is not fully utilised. In addition, in adverse situations like near stall, the aircraft develops significant non-linearities, and linear control laws do not perform well. This study therefore considers the design of a longitudinal flight controller for a fixed-wing aircraft using non-linear dynamic inversion technique or, in terms of control theory, partial exact feedback linearisation. A novel contribution of this study is the proposed combination of three different automatic flight controllers that provide complete 3-DOF longitudinal control. A detailed analysis of the internal dynamics for each controller is also presented. It has been shown that for each controller the internal dynamics are stable. This makes the controller suitable for various flight conditions. The aims of these flight controllers are threefold. RIV BC FORD0 20000 FORD1 20200 FORD2 20205 reportyear 2018 num_of_auth 2 mrcbC52 4 A hod 4ah 20231122142531.3 inst_support RVO:67985556 permalink http://hdl.handle.net/11104/0272688 cooperation ARLID cav_un_auth*0305697 name Czech Technical University in Prague, Faculty of Electrical Engineering, Department of Measurement institution FEL CVUT v Praze country CZ mrcbC64 1 Department of Control Theory UTIA-B 20205 AUTOMATION & CONTROL SYSTEMS confidential S mrcbC86 3+4 Article Automation Control Systems|Engineering Electrical Electronic|Instruments Instrumentation mrcbC86 3+4 Article Automation Control Systems|Engineering Electrical Electronic|Instruments Instrumentation mrcbC86 3+4 Article Automation Control Systems|Engineering Electrical Electronic|Instruments Instrumentation mrcbT16-e AUTOMATIONCONTROLSYSTEMS|ENGINEERINGELECTRICALELECTRONIC|INSTRUMENTSINSTRUMENTATION mrcbT16-j 0.897 mrcbT16-s 1.416 mrcbT16-B 69.091 mrcbT16-D Q2 mrcbT16-E Q1 arlyear 2017 mrcbTft \nSoubory v repozitáři: celikovsky-0476150.pdf mrcbU14 85024485443 SCOPUS mrcbU24 PUBMED mrcbU34 000405681300001 WOS mrcbU56 článek 4.38 MB mrcbU63 cav_un_epca*0320539 IET Control Theory and Applications 1751-8644 1751-8652 Roč. 11 č. 12 2017 1849 1861