The pitch control system of an aircraft is shown in Fig. D5.5. Sketch the root locus for

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The pitch control system of an aircraft is shown in Fig. D5.5. Sketch the root locus for K ranging from 0 to \(\infty\). Determine the value of \(\mathrm{K}\) so that damping ratio of dominant poles is 0.6 . What is location of corresponding poles.

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