A Hover Attitude Control System on A Quad Tilt Wing Unmanned Aerial Vehicle using Linear Quadratic Regulator Method

Quad Tilt Wing Unmanned Aerial Vehicle (QTW UAV) can fly Vertical
Take-Off and Landing (VTOL) and also horizontally (Cruise). The QTW UAV can fly
near a stationary state during hover. Stationary flying can be done by maintaining the
orientation of the Euler angle of the rollers and pitch at 0◦, the yaw angle in a particular
direction, and the altitude (on the vertical axis of the earth). QTW UAV requires a
control system that can maintain a stationary state. The Linear Quadratic Regulator
(LQR) method is one of the control systems to maintain a stationary state. This ability
is done in order to minimize the error response approaching zero. The LQR method uses
the state as feedback to control the attitude of the UAV. The simulation of the QTW
UAV model was carried out to obtain the test results of the control system method.