Page 241 - Neural Network Modeling and Identification of Dynamical Systems

232 RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS

FIGURE A.6 The results of a computational experiment for the MRAC-type control system without the compensator (top
pair of graphs) and with the compensator (bottom pair of graphs) for the hypersonic research vehicle X-43, flight mode M = 6,
in the event of a failure situation at time t = 20 sec (backwards shift of the aircraft center of gravity by 5%). 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; t is
time, sec (see α ref and δ e, act signals related to these cases in Fig. A.7).