ACADSTAFF UGM
| Title | : | A Hover Attitude Control System On A Quad Tilt Wing Unmanned Aerial Vehicle Using Linear Quadratic Regulator Method |
| Author | : |
Ariesta Martiningtyas Handayani, S.Si., M.Cs. (1) Dr.techn. Ahmad Ashari, M.I.Kom. (2) Prof. Dr. Ir. Jazi Eko Istiyanto, M.Sc. (3) |
| Date | : | 0 2023 |
| Keyword | : | QTW UAV LQR ,LQR,Hover,Stationer,Error Response QTW UAV LQR ,LQR,Hover,Stationer,Error Response |
| Abstract | : | 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. |
| Group of Knowledge | : | Sistem Informasi Geografi (SIG) |
| Original Language | : | English |
| Level | : | Internasional |
| Status | : |
Published
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