Control Systems Engineering
7th Edition
ISBN: 9781118170519
Author: Norman S. Nise
Publisher: WILEY
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Chapter 1, Problem 3P
An aircraft's attitude varies in roll, pitch, and yaw as defined in Figure Pl .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 agyro and compares the actual roll angle w ith 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]
FIGURE Pl.2 Aircraft attitude defined
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Chapter 1 Solutions
Control Systems Engineering
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