TY  - JOUR
T1  - Integral Modified Linear Quadratic Regulator Method for Controlling
Lateral Movement of Flying Wing in Rotational Roll Mode
AU - Priyambodo, Tri Kuntoro 
JO  - Journal of Engineering and Applied Sciences
VL  - 13
IS  - 2
SP  - 463
EP  - 471
PY  - 2018
DA  - 2001/08/19
SN  - 1816-949x
DO  - jeasci.2018.463.471
UR  - https://makhillpublications.co/view-article.php?doi=jeasci.2018.463.471
KW  - Autonomous flight control
KW  -integral modified LQR
KW  -stability
KW  -steady state error
KW  -experiments
KW  -UAV
AB  - The studies on fix wing Unmanned Aerial Vehicle (UAV), especially, flying wing type has progressed
very rapidly. Therefore, fix-wing UAV can be used to support disaster mitigation and monitoring. But in order
to make UAV completes the mission, it needs an autonomus flight control system. There were two types of
control method in order to control the movement of flying wing, i.e., longitudinal and lateral. Control of lateral
motion is considered more important because it serves to prevent air turbulence that can cause the air to move
is not in accordance with the mission that has been set. This research aims to design control lateral movement
that is focused on using the roll rotational motion mode control method Linear Quadratic Regulator (LQR) with
the addition of integral in dealing with steady state error that occurred. Experiments conducted by simulating
the model airframe using DATCOM and control simulation using MATLAB. The results showed that by using
modifeied LQR control with integral components added, the system is able to stabilize the rotational motion roll
in a short time and minimal overshoot. In addition, the experiment also showed that steady-state error in the
system can be eliminated with a rise time = 0.189 sec, overshoot = 0.688%, settling time = 0.301 sec and steady
state error = 0%.
ER  -