S. No.:Given the block-diagram representation of an airplane's pitch angle feedback control system,calculate the range of gain K value for the stable operation of the aircraft using Routh -Hurwitz method.

Develop the root-locus of this system as a function of K using computer.Also determine the gain value for the damping ratio = 0.707.Compute the step response of the closed-loop system for this value of gain K. Compare it with the step response of an equivalent second-order system based on dominant poles.Develop a state variable model for this system using the previous value of gain K. Use this state variable model to find output response for a unit step.