Synthesis of Control Law Based on Nonlinear Dynamic Inversion for Supersonic Aircraft in Presence of Noise and Uncertainties

Abstract

In this paper, the approach for synthesis of control law based on nonlinear dynamic inversion (NDI) via feedback linearization combined with Proportional–integral–derivative (PID) controller in outer loop to control supersonic aircraft in its most challenging flight task, i.e., landing in the presence of uncertainty in knowledge of model, measurement noise is developed. The results obtained demonstrate higher control accuracy, lower pilot workload compared to PI in tracking task of pitch angle of a supersonic passenger aircraft in presence of uncertainties, noise and in case of control surface faults.