Page 236 - Neural Network Modeling and Identification of Dynamical Systems

APPENDIX
A

Results of Computational Experiments

With Adaptive Systems

FIGURE A.1 The results of a computational experiment for an MRAC-type control system applied to the hypersonic
research vehicle X-43 for estimating the influence of the natural frequency ω rm of the reference model (ω rm = 2;stepwise
reference signal on the angle of attack; flight mode M = 6, H = 30 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 command signal of the actuator (dotted line) and angle of deflection of elevons (solid line), deg; dδ e /dt is the angular
velocity of the deflection of the elevons, deg/sec; t is time, sec.

227