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264                 RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS
















































                         FIGURE A.38 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 the event of a failure situation at time t = 5 sec (backwards shift of the center of gravity by
                         10%) and then at the time t = 10 sec (50% decrease in the effectiveness of the longitudinal control organ). 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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