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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

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
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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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
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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