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