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

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

Estimation of Aerodynamic Parameters in Conditions of Measurement

The paper discusses the problem of aircraft parameter identification in conditions of measurement noises. It is assumed that all the signals involved into the process of identification are subjects to measurement noises, that is measurement random errors normally distributed. The results of simulation are presented which show the relation between the noises standard deviations and the accuracy of identification

Estimation of Aerodynamic Parameters in Conditions of Measurement

The paper discusses the problem of aircraft parameter identification in conditions of measurement noises. It is assumed that all the signals involved into the process of identification are subjects to measurement noises, that is measurement random errors normally distributed. The results of simulation are presented which show the relation between the noises standard deviations and the accuracy of identification