Analisis Sistem Kestabilan Posisi Pada Wahana Terbang Roket EDF Menggunakan Sensor 9 DOF IMU

Abstract

Aviation and space technology is one of the leading technologies for developed countries, especially technology of rocket. Therefore the rocket requires a control system that is able to control sensor data which is processed into filtered. This case will analyze the rocket control system using the Inertial Measurement Unit (IMU) sensor which consists of an Accelerometer, Gyroscope and Magnetometer. The condition value generated by the sensor in the form of roll, pitch and yaw will be filtered using kalman filter.  The study will analyze the Electric Ducted Fan (EDF) rocket stability system through the results of sensors filtered using kalman filter to obtain stability in the IMU sensor output. The level of stability will be obtained from the standard deviation generated between sensor data using kalman filters and without kalman filters. The results of roll without using kalman filter have a standard deviation of 4.7°. The results of roll using kalman filter have a standard deviation of 2.4°. The results of pitch without using kalman filter have a standard deviation of 4.2°. The results of pitch using kalman filter have a standard deviation of 1.8°. The results of yaw without using kalman filter have a standard deviation of 2.47°. The results of yaw using kalman filter have a standard deviation of 0.59°. Conclusion of this study is that filters can work effectively to improve the stability of the IMU sensor output.