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238                 RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS




















































                         FIGURE A.12 The results of a computational experiment for a model reference control system with a compensator for the
                         sequence of stepwise reference signals (hypersonic aircraft X-43, flight regime M = 6, variant No. 3). Here α is angle of attack,
                         deg (dotted line for reference model, solid line for plant); E α is the angle of attack tracking error, deg; α ref is the angle of
                         attack reference signal, deg; δ e, act is command signal for the elevator actuator, deg; t is time, sec.
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