On the internal stability of non-linear dynamic inversion: application to flight control

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F67985556%3A_____%2F17%3A00476150" target="_blank" >RIV/67985556:_____/17:00476150 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/68407700:21230/17:00311425

Výsledek na webu

<a href="http://dx.doi.org/10.1049/iet-cta.2016.1067" target="_blank" >http://dx.doi.org/10.1049/iet-cta.2016.1067</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1049/iet-cta.2016.1067" target="_blank" >10.1049/iet-cta.2016.1067</a>

Jazyk výsledku

angličtina

Název v původním jazyce

On the internal stability of non-linear dynamic inversion: application to flight control

Popis výsledku v původním jazyce

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.

Název v anglickém jazyce

On the internal stability of non-linear dynamic inversion: application to flight control

Popis výsledku anglicky

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.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20205 - Automation and control systems

Projekt

<a href="/cs/project/GA17-04682S" target="_blank" >GA17-04682S: Řízení kráčejících robotů metodou sladěných virtuálních holonomních omezení</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2017

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

IET Control Theory and Applications

ISSN

1751-8644

e-ISSN

—

Svazek periodika

11

Číslo periodika v rámci svazku

12

Stát vydavatele periodika

GB - Spojené království Velké Británie a Severního Irska

Počet stran výsledku

13

Strana od-do

1849-1861

Kód UT WoS článku

000405681300001

EID výsledku v databázi Scopus

2-s2.0-85024485443