The transfer function from the thrust deflection angle u to the pitch angle of a guided missile is found to be G(s). The configuration of the overall system is chosen as shown in the figure. The transfer function of the actuator is G₁ (s) = 1/(s+ 6.1) and K₂ = 1. Determine gain K₁ for stability and the value of gain K₁such that the position error is less than 10%, the overshoot is less than 15%, and the settling time is less than 10 seconds. K₁ R(s) G(s)= Actuator Missile ☹(s) G₁ (s) G(s) K₂ s 4(s + 0.05) s(s+2) (s-1.2)