PEMODELAN SISTEM KENDALI PITCH ATTITUDE PADA
PESAWAT BOEING 747 DENGAN MENGGUNAKAN LAG
COMPENSATOR
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Efata Kwek, Yustino
Subject
T Technology (General)
Datestamp
2024-05-30 08:41:13
Abstract :
Modern airplanes today have experienced very rapid development, it can be seen from a variety of systems that are very complex in a modern aircraft, one of the developing systems is a system in controlling the aircraft itself or what is often referred to as the autopilot system. Pitching motion is the movement of an aircraft based on the horizontal axis so that the movement that occurs is an up and down motion on the front of the plane like a nodding movement that is governed by an elevator at the tail of the plane. This study designed a pitch attitude system that is able to produce faster stability based on matlab. To design the pitch attitude system starting with the aircraft's longitudinal motion data retrieval, which will then be changed to the transfer function of the pitch motion, after obtaining the results of the unstable pitch attitude, a compensator is made to accelerate the stability of the pitch attitude motion in this thesis research. lag compensator. Of the ten tests carried out, the one that experienced the largest increase was during the tenth experiment which was able to increase the value of the steady state error with an increase of 9.2335% without changing the transient response of the pitch attitude control system.
Modern airplanes today have experienced very rapid development, it can be seen from a variety of systems that are very complex in a modern aircraft, one of the developing systems is a system in controlling the aircraft itself or what is often referred to as the autopilot system. Pitching motion is the movement of an aircraft based on the horizontal axis so that the movement that occurs is an up and down motion on the front of the plane like a nodding movement that is governed by an elevator at the tail of the plane. This study designed a pitch attitude system that is able to produce faster stability based on matlab. To design the pitch attitude system starting with the aircraft's longitudinal motion data retrieval, which will then be changed to the transfer function of the pitch motion, after obtaining the results of the unstable pitch attitude, a compensator is made to accelerate the stability of the pitch attitude motion in this thesis research. lag compensator. Of the ten tests carried out, the one that experienced the largest increase was during the tenth experiment which was able to increase the value of the steady state error with an increase of 9.2335% without changing the transient response of the pitch attitude control system.
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