An aircraft’s attitude varies in roll, pitch, and yaw as defined in Figure. 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.

Transcribed Image Text:

Pitch angle Aileron deflection up Aileron deflection down Roll angle Yaw angle