3. An aircraft's attitude varies in roll, pitch, and yaw as defined in Figure P1.2. Draw a functional block diagram for a closed-loop system that stabilizes the roll as follows: The system measures the actual roll angle with a gyro and compares the actual roll angle with the desired roll angle. The ailerons respond to the roll-angle error by undergoing an angular deflection. The aircraft responds to this angular deflection, producing a roll angle rate. Identify the input and output transducers, the controller, and the plant. Further, identify the nature of each signal. [Section 1.4: Introduction to a Case Study] Roll angle X Pitch angle Aileron deflection up Yaw angle Aileron deflection down FIGURE P1.2 Aircraft attitude defined
3. An aircraft's attitude varies in roll, pitch, and yaw as defined in Figure P1.2. Draw a functional block diagram for a closed-loop system that stabilizes the roll as follows: The system measures the actual roll angle with a gyro and compares the actual roll angle with the desired roll angle. The ailerons respond to the roll-angle error by undergoing an angular deflection. The aircraft responds to this angular deflection, producing a roll angle rate. Identify the input and output transducers, the controller, and the plant. Further, identify the nature of each signal. [Section 1.4: Introduction to a Case Study] Roll angle X Pitch angle Aileron deflection up Yaw angle Aileron deflection down FIGURE P1.2 Aircraft attitude defined
Introductory Circuit Analysis (13th Edition)
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Author:Robert L. Boylestad
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Chapter1: Introduction
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I have a question in my home work related Control System Lesson. The following below is my question.
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![3. An aircraft's attitude varies in roll, pitch, and yaw as
defined in Figure P1.2. Draw a functional block diagram
for a closed-loop system that stabilizes the roll as follows:
The system measures the actual roll angle with a gyro and
compares the actual roll angle with the desired roll angle.
The ailerons respond to the roll-angle error by undergoing
an angular deflection. The aircraft responds to this angular
deflection, producing a roll angle rate. Identify the input
and output transducers, the controller, and the plant.
Further, identify the nature of each signal. [Section 1.4:
Introduction to a Case Study]
Roll angle
X
Pitch angle
Aileron
deflection up
Yaw angle
Aileron
deflection down
FIGURE P1.2 Aircraft attitude defined](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fee789098-4905-4a95-b835-85874aef6f66%2F3822730d-d374-4f41-8cae-8c9b015fc1e7%2Fc1j86ps_processed.jpeg&w=3840&q=75)
Transcribed Image Text:3. An aircraft's attitude varies in roll, pitch, and yaw as
defined in Figure P1.2. Draw a functional block diagram
for a closed-loop system that stabilizes the roll as follows:
The system measures the actual roll angle with a gyro and
compares the actual roll angle with the desired roll angle.
The ailerons respond to the roll-angle error by undergoing
an angular deflection. The aircraft responds to this angular
deflection, producing a roll angle rate. Identify the input
and output transducers, the controller, and the plant.
Further, identify the nature of each signal. [Section 1.4:
Introduction to a Case Study]
Roll angle
X
Pitch angle
Aileron
deflection up
Yaw angle
Aileron
deflection down
FIGURE P1.2 Aircraft attitude defined
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