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

0476150 - ÚTIA 2018 RIV GB eng J - Journal Article
Alam, M. - Čelikovský, Sergej
On the internal stability of non-linear dynamic inversion: application to flight control.
IET Control Theory and Applications. Roč. 11, č. 12 (2017), s. 1849-1861. ISSN 1751-8644. E-ISSN 1751-8652
R&D Projects: GA ČR(CZ) GA17-04682S
Institutional support: RVO:67985556
Keywords : flight control * non-linear dynamic inversion * stability
OECD category: Automation and control systems
Impact factor: 3.296, year: 2017
http://library.utia.cas.cz/separaty/2017/TR/celikovsky-0476150.pdf

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.
Permanent Link: http://hdl.handle.net/11104/0272688