ADAPTIVE CONTROL SYSTEM OF A NON-LINEAR ELASTIC AIRCRAFT, BUILT-UP BY THE METHOD OF A SEQUENTIAL COMPENSATOR

The problem of preventing the occurrence and development of the flexural-torsional flutter of the aircraft wings by forced suppression of nonlinear elastic torsional oscillations of the wings by means of adaptive control is considered. A nonlinear mathematical model of the aircraft longitudinal motion is developed, taking into account the torsional air augeness of the wings. An adaptive system for controlling the longitudinal motion of a nonlinear elastic aircraft (LA) has been developed and investigated. To represent the nonlinear mathematical model of longitudinal motion of an aircraft in the form of an input-output for the application of the method of a sequential compensator, partial linearization of the model was required. The conducted computer research demonstrated the satisfactory efficiency of the constructed adaptive control system for the output in suppression of nonlinear aeroelastic torsional oscillations of the aircraft wings.

Authors: V. V. Putov, V. N. Sheludko, V. F. Nguen, А. V. Putov, N. D. Than

Direction: Automation and Control

Keywords: Aircraft, longitudinal motion, nonlinear mathematical model, taking into account aeroelasticity, flexural–torsion wing flutter, majorizing function method, adaptive control systems by state, observer application, suppression of aeroelastic wings oscillation, wind disturbances of flight

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