7.12. The transfer function from the thrust deflection angle u to the pitch angle θ of a guided missile is found to be:
4(s + 0.05)
G(s)
s(s + 2)(s - 1.2)
The configuration of the compensator is chosen as shown in Figure P7.12. The transfer function of the actuator is G(s) = 1/(s + 6.1). If k1 = 2k2, find a k1, if it exists, such that the position error is less than 10%, the overshoot is less than 15%, and the settling time is less than 10 seconds.
Actuator
Missile
G(s)
G(s)
Figure P7.12