Question: 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

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 are Ta 1.0, (wa = = 1.0, and K = 0.8, = 5. Design 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.

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

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The loop transfer function is We desire dominant roots with T s 5 sec and PO 5 so use 069 and n ... View full answer

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