Page 278 - Neural Network Modeling and Identification of Dynamical Systems

RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS 269

FIGURE A.43 The results of a computational experiment for the MPC-type control system applied to the hypersonic
research vehicle with a stepwise reference signal on the angle of attack (flight mode M = 6, H = 28 km). 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; q is the
pitch angular velocity, deg/sec; δ e is the command signal of the actuator (dotted line) and the deflection angle of the elevons
(solid line), deg; dδ e /dt is the angular velocity of the deflection of the elevons, deg/sec; t is time, sec.