Adaptive Motion Control of a Non-Linear Elastic Aircraft

This article covers the task of designing and researching an adaptive control system for the longitudinal motion of light and ultralight aircrafts that considers non-linear torsional aeroelasticity of the wing as an essential component of the two-frequency unstable periodic flexural-torsional wing flutter and torsional elasticity of elevator transmission. The article describes conditions for dissipativity (robustness) of the designed adaptive system and a computer simulation of its efficiency in terms of forced suppression of wings and rudder elastic oscillations and simultaneous retaining of fast response time and satisfactory dynamic accuracy under the conditions of large uncertainty of inertia parameters, elasticity coefficients and non-linear aerodynamic properties of an aircraft.