PERANCANGAN SISTEM KONTROL LEAD COMPENSATOR
UNTUK MENGENDALIKAN PITCH ATTITUDE AUTOPILOT
PESAWAT BOEING 747
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Yudhi Adventi, Barbara
Subject
T Technology (General)
Datestamp
2024-05-30 01:47:59
Abstract :
Pitch attitude is a longitudinal problem that is controlled by elevators, elevators are usually located at the rear of the plane parallel to the wing which is also where the aileron is located. This study presents the pitch attitude control design needed to overcome the longitudinal dynamic characteristics using the Lead Compensator controller. In designing the pitch attitude system, it starts by processing longitudinal motion parameter data, the data is used to find the State space. After the state space is obtained, the transfer function will be searched. After that the system design simulation is made using the root locus and will be stabilized by the lead compensator. Simulation results show that the system has decreased overshoot ranging from 10.24% ? 40.39%. The decrease in settling time ranged from 25% ? 55%. The rise time delay ranges from 25.7% ? 80%. Steady state error ranges from -112.5% ? 37.5%.
Pitch attitude is a longitudinal problem that is controlled by elevators, elevators are usually located at the rear of the plane parallel to the wing which is also where the aileron is located. This study presents the pitch attitude control design needed to overcome the longitudinal dynamic characteristics using the Lead Compensator controller. In designing the pitch attitude system, it starts by processing longitudinal motion parameter data, the data is used to find the State space. After the state space is obtained, the transfer function will be searched. After that the system design simulation is made using the root locus and will be stabilized by the lead compensator. Simulation results show that the system has decreased overshoot ranging from 10.24% ? 40.39%. The decrease in settling time ranged from 25% ? 55%. The rise time delay ranges from 25.7% ? 80%. Steady state error ranges from -112.5% ? 37.5%.
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