@inproceedings{d239ad048256491494b0608dab5864ee,
title = "Spatial flight control of aircraft model based on the dynamic contraction method",
abstract = "In the paper the design of an aircraft flight controller based on the Dynamic Contraction Method is presented. The control task is formulated as a tracking problem of aerodynamic state variables: velocity of flight and three angles, which are responsible for aircraft flight conditions. The applied DCM method allows to create expected outputs for non-linear and non-stationary objects in spite of incomplete information about varying parameters of the system and external disturbances. The resulting controller has a simple form of a combination of a low-order linear dynamical system and a matrix whose entries depend nonlinearly on certain measurable flight variables. Simulation results for a F-16 model confirm theoretical expectations.",
author = "Roman Czyba and B{\l}achuta, \{Marian J.\}",
year = "2001",
doi = "10.2514/6.2001-4087",
language = "English",
isbn = "9781563479786",
series = "AIAA Guidance, Navigation, and Control Conference and Exhibit",
publisher = "American Institute of Aeronautics and Astronautics Inc.",
booktitle = "AIAA Guidance, Navigation, and Control Conference and Exhibit",
note = "AIAA Guidance, Navigation, and Control Conference and Exhibit 2001 ; Conference date: 06-08-2001 Through 09-08-2001",
}