TY - JOUR N2 - This paper presents the design of digital controller for longitudinal aircraft model based on 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. L1 - http://www.czasopisma.pan.pl/Content/111270/PDF/06_art_ACS-2019-1_INTERNET.pdf L2 - http://www.czasopisma.pan.pl/Content/111270 PY - 2019 IS - No 1 EP - 109 DO - 10.24425/acs.2019.127525 KW - nonlinear systems KW - MIMO systems KW - aircraft control KW - digital controller KW - singular perturbation A1 - Czyba, Roman A1 - Stajer, Lukasz PB - Committee of Automatic Control and Robotics PAS VL - vol. 29 DA - 2019.03.28 T1 - Dynamic Contraction Method approach to digital longitudinal aircraft flight controller design SP - 97 UR - http://www.czasopisma.pan.pl/dlibra/publication/edition/111270 T2 - Archives of Control Sciences ER -