Robust quasi NID aircraft 3D flight control under sensor noise
Kybernetika, Tome 35 (1999) no. 5, p. [637].

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In the paper the design of an aircraft motion controller based on the Dynamic Contraction Method is presented. The control task is formulated as a tracking problem for Euler angles, where the desired decoupled output transients are accomplished under assumption of high-level, high-frequency sensor noise and 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.
Classification : 93B35, 93B51, 93C73, 93C95
Mots-clés : dynamic contraction method; tracking problem; aircraft motion controller; low-order linear dynamical system; decoupled output transients; sensor noise 
@article{KYB_1999__35_5_a5,
     author = {B{\l}achuta, Marian J. and Yurkevich, Valery D. and Wojciechowski, Konrad},
     title = {Robust quasi {NID} aircraft {3D} flight control under sensor noise},
     journal = {Kybernetika},
     pages = {[637]},
     publisher = {mathdoc},
     volume = {35},
     number = {5},
     year = {1999},
     mrnumber = {1728472},
     zbl = {1274.93094},
     language = {en},
     url = {https://geodesic-test.mathdoc.fr/item/KYB_1999__35_5_a5/}
}
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Błachuta, Marian J.; Yurkevich, Valery D.; Wojciechowski, Konrad. Robust quasi NID aircraft 3D flight control under sensor noise. Kybernetika, Tome 35 (1999) no. 5, p. [637]. https://geodesic-test.mathdoc.fr/item/KYB_1999__35_5_a5/