Solution Manual For control systems engineering 6th Edition By Norman

SOLUTION
MANUAL
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ISBN13 978-0470-54756-4




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& Sons,

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Introduction
ANSWERS TOREVIEWQUESTIONS .z




1. Guided missiles, automatic gain control in radio receivers, satellite tracking antenna
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2. Yes - power gain, remote control, parameter conversion; No - Expense, complexity
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3. Motor, low passfilter, inertia supported between two bearings
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4. Closed-loop systems compensate for disturbances by measuring the response, comparing it
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bg to the input response (the desired output), and then correcting the output response.
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5. Under the condition that the feedback element is other than unity
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6. Actuating signal .z




7. Multiple subsystems can time share the controller. Any adjustments to the controller
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bg can be i mplemented with simply software changes.
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8. Stability, transientresponse, andsteady-stateerror bg bg




9. Steady-state,transient
10. It follows a growing transient response until the steady-state response is no longer
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bg visible. Thesystem will either destroy itself, reach an equilibrium state because of saturation
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bg in driving amplifiers, or hit limit stops.
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11. Naturalresponse
12. Determine the transientresponse performance of the system. bg bg bg bg bg bg




13. Determine system parameters to meet the transient response specificationsfor the system.
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14. True
15. Transfer function, state-space, differential equations bg bg bg bg




16. Transfer function - the Laplace transform of thedifferential equation .z bg bg bg .z bg bg




State-space - representation of an nth order differential equation as n simultaneous first-
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orderdifferential equations
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Differential equation - Modeling a systemwith its differential equation
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SOLUTIONSTOPROBLEMS
50volts
1. Five turns yields 50 v. Therefore K =
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= 1.59
5x2 
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Copyright © bg b g b g 2011 by John Wiley bg bg bg


& Sons,

, 1-2 b g b g Chapter Introduction
1:




2.



Desired Temperature Voltage Actual
.z
Fuelflo
temperatu differenc differen
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temperatu
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Amplifier
Thermostat andvalve
Heater
+ s
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-


3.



Desired Input Error Aileron Roll Roll
roll voltag
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angl
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e
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e
Pilot +
.z
Aileron .z
Aircraft
Integrate
control
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positi
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dynami
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on c s
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control
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Gyro
Gyro voltage bg




4.

Input
Speed
Desired volta
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Actual
Error
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speed g e bg
spe
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volta
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transducer Amplifier ed
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e
system
-
Dancer
positio
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Dancer
Voltage n dynami
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proportion
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to actual speed
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Copyright © bg b g b g 2011 by John Wiley
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& Sons,