1. In the system of Figure P9.1, it is desired to have a step responsewith zero steady-state error, and a closed-loop damping ratio if 0.5.The open loop transfer function isKG(s) =(s+ 2)²(s+20)Design a PI controller for the given specifications. Compare theperformance of the uncompensated and compensated systems.[Section: 9.2]R(s)E(s)C(s)G(s)FIGURE P9.1

Answered: 1. In the system of Figure P9.1, it is…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Q5) For unity feedback control system with forward transfer function (G(s) ): G(s) = ; By using root locus graph calculate the value K(s+5) (s+2)(s²+12s+50) of gain (K) which must be added to get the dominant root at damping ratio (-0.886) and natural frequency (w = 8 rad/sec )? www CTRICAL ENGIN
root locus electrical engineering Don't overthink and reject. Complete the solution as per the given transfer function. No need of quadratic equation just simplify for the exact given transfer function.
A second order plant with unity feedback is cascaded by a proportional controller as shown. If K is 100, 1. HI. Determine its closed-loop poles Y(s)/R(s). Determine its transfer function of E(s)/R(s) Calculate the steady state error of the following block diagram for a unit step R(s) input. iv. Suggest a method to improve on the steady state error. E(s) K pito 7 (s+2)(s+5) Y(s)
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22 Q2 A PID controller is designed to control the robot leg, and the control system is shown in Figure 2. (a) Find the transfer function (s)/R(s). (b) R(s) [15 marks] Use the Routh-Hurwitz stability criterion to determine the range of the parameter K such that the closed-loop system is stable. + K 2+-+s S PID Controller Figure 2 4 s² + 3s + 4 Robot Leg dynamics [25 marks] ℗(s)
1) Consider the system below: Vehicle Controller Steering dynamics Desired Actual bearing angle bearing angle 50 1 K s2 + 10s + 50 s(s + 5) Figure 1: Simplified Block Diagram of a Self-Guiding Vehicle's Bearing Angle Control. • Find a K value that the system has minimum rise time and minimum overshoot. Let us call this proportional gain as Kopt Show each step while finding Kopt- Show the necessary graphical solutions. Simulate the system response with 3 different K values. (Kopt and two other K values close to Kopt) Show the system response (actual bearing angle) in a single graph for different K values. • Comment on the results.
block diagram pls solve fast As Simplify the multiple loop feedback control system? R(s) G₁ G₂ H3 H₂ + G3 H₁ G₁ Y(s)
The arm angle, e (t), is controlled by a closed-loop system. The input (reference) to the system is the desired angle, and the output is the actual angle. A controller uses the difference between the desired angle and the actual angle to drive the motor, resulting in a motor torque applied to the system. motor torque(t) houlder joint damping(B) The customer wants to make a system to have 1) O steady-state error 2) Less than 10% overshoot 3) Less than 1- For a step inp **ling time Arm length (/) Mass(m) g design a controller to meet the design spec above. 1) Design a controller to meet the design spec. 2) Evaluate your controller using step response (time response) 3) Evaluate your closed-loop system using frequency response (e.g., Bandwidth, Gain margin. Phase margin).
For the system with open loop transfer function given by R(s) K s(s + 1) (s² + 4s +13) where K is the feedback gain. Sketch the root locus a) How many asymptotes are there for this system's root locus? what are asymptote angles? What is the center of asymptotes? C(s) b) Does the root locus cross the imaginary axis? where and what is the value of K at that point? c) Is there any break away, break in points? What is the approximate values of these points?
2.2 Please answer the best you can.
2. Sketch the general shape of the root locus for each of the open-loop pole-zero plots shown in Figure P8.2. [Section: 8.4] jo) s-plane ° ja) *s-plane (a) (b) *s-plane * 3-plane (c) (d) jav ja) s-plane splane

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