Dynamic Contraction Method approach to digital longitudinal aircraft flight controller design

• Autorzy: Czyba Roman , Stajer Lukasz

Identyfikatory

DOI

10.24425/acs.2019.127525

• Języki publikacji: EN

Abstrakty

EN

This paper presents the design of digital controller for longitudinal aircraft model basedon the Dynamic Contraction Method. The control task is formulated as a tracking problem of velocity and flight path angle, where decoupled output transients are accomplished in spite of incomplete information about varying parameters of the system and external disturbances. The design of digital controller based on the pseudo-continuous approach is presented, where the digital controller is the result of continuous-time controller discretization. A resulting output feedback controller has a simple form of a combination of low-order linear dynamical systems and a matrix whose entries depend nonlinearly on certain known process variables. Simulation results for an aircraft model confirm theoretical expectations.

Słowa kluczowe

EN

nonlinear systems; MIMO system; aircraft control; digital controller; singular perturbation

• Wydawca: Polish Academy of Sciences, Committee of Automatic Control and Robotics
• Czasopismo: Archives of Control Sciences
• Rocznik: 2019
• Tom: Vol. 29, No. 1
• Strony: 97--109
• Opis fizyczny: Bibliogr. 8 poz., rys., wykr., wzory

Twórcy

autor

Czyba Roman

• Silesian University of Technology, 16 Akademicka St., Gliwice 44-100, Poland

autor

Stajer Lukasz

• Silesian University of Technology, 16 Akademicka St., Gliwice 44-100, Poland

Bibliografia

• [1] R. Austin: Unmanned Aircraft Systems – UAVS Design, Development and Deployment. John Wiley & Sons, 2010.
• [2] R. Czyba, M. Blachuta: Dynamic ContractionMethod approach to robust longitudinal flight control under aircraft parameters variations. Proceedings of the AIAA Guidance, Navigation and Control Conference, AIAA Paper No 2003–5554, Austin, USA, 2003.
• [3] J. Liu, X. Wang: Advanced Sliding Mode Control for Mechanical Systems. Springer, Berlin, Heidelberg, 2011.
• [4] S. Sieberling, Q. P. Chu, J. A.Mulder: Robust Flight Control Using Incremental Nonlinear Dynamic Inversion and Angular Acceleration Prediction. J. of Guidance, Control, and Dynamics, 33(6) (2010), 1732–1742.
• [5] B. Stevens, F. Lewis: Aircraft control and simulation. John Wiley & Sons, New York, 1992.
• [6] K. P. Valavanis: Advances in Unmanned Aerial Vehicles. Springer, Netherlands, 2007.
• [7] A. S. Vostrikov, V. D. Yurkevich: Design of control systems by means of localization method. Preprints of 12-th IFAC World Congress, Sydney, 8 (1993), 47–50.
• [8] V. D. Yurkevich: Design of Nonlinear Control Systems with the Highest Derivative in Feedback. World Scientific Publishing, Singapore, 2004.

Uwagi

PL

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).