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Optimization for PID Control Parameters on Pitch Control of Aircraft Dynamics Based on Tuning Methods |
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PP: 343-350 |
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doi:10.18576/amis/100136
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Author(s) |
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G. Sudha,
S. N. Deepa,
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Abstract |
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| Today many aircraft control systems and process control industries are employing classical controller such as Proportional
Integral Derivative Controller (PID) to improve the system characteristics and dynamic performance. To improve the stability analysis
and system performance of an aircraft, PID controller is employed in this paper. The safety of flight envelope can be improved by
tuning parameters of PID controller for pitch control dynamics of an aircraft. Designing the mathematical model is necessary and
important to describe the longitudinal pitch control of general aviation aircraft system. PID controller is developed based on dynamic
and mathematical modeling of an aircraft system. The various tuning methods such as Zeigler-Nichols method (ZN),Modified Zeigler-
Nichols method, Tyreus- Luyben tuning and Astrom-Hagglund tuning methods are evaluated for general aviation aircraft system. The
simulation results prove that PID controller parameters tuned by ZN method for general aviation aircraft dynamics is better compared
to the other methods in improving the stability and performance of flight in all conditions such as climb, cruise and approach phase. |
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