Robust quasi NID aircraft 3D flight control under sensor noise

In the paper the design of an aircraft motion controller based on the Dynam ic Contraction Method is presented. The control task is formulated as a tra cking problem for Euler angles, where the desired decoupled output transien ts are accomplished under assumption of high-level, high-frequency sensor n oise and incomplete information about varying parameters of the system and external disturbances. The resulting controller has a simple form of a comb ination of a low-order linear dynamical system and a matrix whose entries d epend nonlinearly on certain measurable flight variables.