3. An aircraft's attitude varies in roll, pitch, and yaw as defined in Figure P1.2. Draw a functional block dia- gram 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
3. An aircraft's attitude varies in roll, pitch, and yaw as defined in Figure P1.2. Draw a functional block dia- gram 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
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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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 dia-
gram 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 trans-
ducers, the controller, and the plant. Further, identify
the nature of each signal. [Section 1.4: Introduction to
a Case Study]
Pitch angle
Roll angle
X
y
Aileron
deflection up
Yaw angle
z
Aileron
deflection down
FIGURE P1.2 Aircraft attitude defined](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F9c0d039d-edd9-453b-b7e3-db8354654c44%2Fb23bbecf-cdee-42da-aea2-918a21fb9559%2Fcalwzc8_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 dia-
gram 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 trans-
ducers, the controller, and the plant. Further, identify
the nature of each signal. [Section 1.4: Introduction to
a Case Study]
Pitch angle
Roll angle
X
y
Aileron
deflection up
Yaw angle
z
Aileron
deflection down
FIGURE P1.2 Aircraft attitude defined
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