A simplified version of the attitude rate control for a supersonic aircraft is shown in Figure P10.3. When the vehicle is flying at four times the speed of sound (Mach 4) at an altitude of 100,000 ft, the parameters areDesign a compensator G_c (s) so that the response to a step input has a percent overshoot of P.O ≤ 5% and a settling time (with a 2% criterion) of T_s ≤ 5 s.

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Ta 1.0, (wa = = 1.0, and K₁ = 0.8, = 5. Wa