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262                 RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS



















































                         FIGURE A.36 The results of a computational experiment for the MRAC-type control system (micro-UAV “003”), a flight
                         with airspeed V ind = 30 km/h in normal operation conditions. Here α is angle of attack, deg (dotted line for reference model,
                         solid line for plant); E α is the tracking error for the given angle of attack, deg; α ref is the reference signal on the angle of
                         attack, deg; δ e, act is the command signal for the elevator actuator, deg; t is time, sec.
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