Control Systems Engineering
Control Systems Engineering
7th Edition
ISBN: 9781118170519
Author: Norman S. Nise
Publisher: WILEY
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Chapter 8, Problem 15P

For the unity feedback system of Figure P8.3, where

G s = K s + 5 s 2 + 1 s 1 s + 3

sketch the root locus and find the range of K such that there will be only two right-half-plane poles for the closed-loop system. [Section: 8.5]

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Q.1 - The open loop transfer function for a unity - feedback systemis G(s)= XL‘ 7xs and r(t)=3t determine steady state error.If it is desired to reduce this existing error by 7% fined new value of gain of the system.
a)is the aircraft stable about the equilibrium represented by the transfer function? b) Using proportional feedback,what is the range of acceptable gains for the closed loop systen to be stable? c) Design a feedback control system that allows the pilot to command a pitch angle with overshoot less than or equal to 4.15% and a natural frequency of greater than or equal to 0.99 rad/s d) Design a feedback control system that allows the pilot to command a pitch angle with the same overshoot and a natural frequency of one half the system in part c.
Given the system equipped with unitary feedback, whose direct branch transfer function is: Design a PID controller with one of the Ziegler-Nichols methods.

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Control Systems Engineering

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