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228                 RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS




















































                         FIGURE A.2 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 = 3;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.
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