Page 288 - Neural Network Modeling and Identification of Dynamical Systems

RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS 279

FIGURE A.53 The results of a computational experiment for the MPC-type control system with compensator (F-16 aircraft,
flight mode with airspeed V ind = 700 km/h). Adaptation to the change in the dynamics of the control object due to failures:
backwards shift of the center by 5% (t = 30 sec); 50% decrease in the effectiveness of the control (t = 60 sec). Here α is angle of
attack, deg (dotted line for reference model, solid line for plant); E α is tracking error for the given angle of attack, deg; α ref
is reference signal on the angle of attack, deg; δ e, act is command signal for the elevator actuator, deg; t is time, sec.