Pendeteksi Sikap pada Model Wahana Terbang menggunakan Inertial Measurement Unit

This journal elaborate the aplication of a gyroscope and accelerometer from an inertial measurement unit (IMU) for sensing attitude on an aircraft. Attitude give 3 (three) basic informations, that information are roll, pitch and yaw. The purpose of this journal is to analys if the attitude sensing device are suitble to be used on a model aircraft. This journal are designing measurement system and monitoring using software from LabVIEW. The method used to detect roll, pitch and yaw is combination from the measurement of gyroscope and accelerometer. The testing of the attitude sensing device by simulating the kinematics of an aircraft. The results shows that the attude sensing device are qualified for sensing tilt angle for x-axis (roll) with standard deviation 0,58 o, sensing tilt angle for y-axis (pitch) with standard deviation 0.53 o and sensing tilit angle for z (axis) with standar deviation 7,64 o.