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

  • Author(s): Mushfiqul Alam 1  and  Sergej Celikovsky 2
    • View affiliations
    • Affiliations: 1: Department of Measurement, Faculty of Electrical Engineering, Technicka 2, Czech Technical University in Prague, Prague, Czech Republic ;
      2: Institute of Information Theory and Automation, Czech Academy of Sciences, Pod Vodarenskou Vezi 4, CZ-182 08 Prague 8, Czech Republic
  • Source: Volume 11, Issue 12, 11 August 2017, p. 1849 – 1861
    DOI:  10.1049/iet-cta.2016.1067 , Print ISSN 1751-8644, Online ISSN 1751-8652
© The Institution of Engineering and Technology
Received 15/08/2016, Accepted 31/03/2017, Revised 21/03/2017, Published 31/03/2017

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. First, to provide control of the flight path angle by tracking the pitch angle and the angle of attack. Second, to provide high attitude (pitch up or down) manoeuvrability. Finally, to provide automatic adverse attitude recovery of the aircraft in situations like stall, the switching strategy between the controllers are also discussed. A simulation carried out on a non-linear model of a multi-role fighter aircraft verified the proposed theoretical results confirming the suitability of the controllers.

Inspec keywords: aircraft control; feedback; aerospace components; military aircraft; linearisation techniques; stability; nonlinear control systems; switching systems (control); control system synthesis; attitude control

Other keywords: pitch angle tracking; automatic flight controllers; flight control laws; high attitude manoeuvrability; 3-DOF longitudinal control; linearised models; switching strategy; nonlinear dynamic inversion technique; partial exact feedback linearisation; control theory; high-fidelity nonlinear model; longitudinal flight controller design; multirole fighter aircraft; linear control laws; attitude recovery; flight path angle control; fixed-wing aircraft; aircraft control; internal dynamics; internal stability

Subjects: Spatial variables control; Time-varying control systems; Stability in control theory; Aerospace control; Vehicle mechanics; Military control systems; Nonlinear control systems; Control system analysis and synthesis methods

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