Consider the second-order model of the aircraft attitude control system shown in Fig. 7-25. The transfer...

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Consider the second-order model of the aircraft attitude control system shown in Fig. 7-25. The transfer function of the process is G,(s) = = 4500 K s(s+ 361.2) (a) Design a series PD controller with the transfer function G.(s) = KD + Kps so that the follow ing performance specifications are satisfied: Steady-state error due to a unit-ramp input ≤0.001 Maximum overshoot ≤ 5 percent Rise time t, ≤ 0.005 sec Settling time t, ≤ 0.005 sec (b) Repeat part (a) for all the specifications listed, and, in addition, the bandwidth of the system must be less than 850 rad/sec. Command Sensor PREAMP Control surface Control surface POWER AMPLIFIER WITH CURRENT FB CIL TACHOMETER CLI DC MOTOR www. GEAR TRAIN Figure 7-25 Block diagram of an attitude-control system of an aircraft. LOAD 0, Position of control surface Consider the second-order model of the aircraft attitude control system shown in Fig. 7-25. The transfer function of the process is G,(s) = = 4500 K s(s+ 361.2) (a) Design a series PD controller with the transfer function G.(s) = KD + Kps so that the follow ing performance specifications are satisfied: Steady-state error due to a unit-ramp input ≤0.001 Maximum overshoot ≤ 5 percent Rise time t, ≤ 0.005 sec Settling time t, ≤ 0.005 sec (b) Repeat part (a) for all the specifications listed, and, in addition, the bandwidth of the system must be less than 850 rad/sec. Command Sensor PREAMP Control surface Control surface POWER AMPLIFIER WITH CURRENT FB CIL TACHOMETER CLI DC MOTOR www. GEAR TRAIN Figure 7-25 Block diagram of an attitude-control system of an aircraft. LOAD 0, Position of control surface