Description
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Abstract
The experiment herein hopes to tune the aircraft’s control system to the extent of addressing the
rolling dynamics, in which case it will affect its dynamic stability. The plane continues to roll
exponentially at a 1 degree input angle.
The controller of the system increased gradually using the Ziegler-Nichols method to achieve a
stable response. The plane stabilized at 5 degrees pilot input. Consequently, the method applies to a real
life situation in cases where closed loop systems keep the aircraft stable at any angle of input, irrespective
of the existing noise within the system.
Discussion and Conclusion
The primary d...