#TITLE_ALTERNATIVE#

• Main Author: HESAPUTRA SURYAWAN (NIM : 13214017), TAFWIDA
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/31212
• Institution: Institut Teknologi Bandung

<p align="justify"> <br /> <br /> Attitude Determination and Control System (ADCS) is a sub-system of attitude controllers commonly used in spacecraft, including satellites. One component of the ADCS is the Attitude Heading References System (AHRS). AHRS serves to obtain attitude information of the satellite. It detects the angle of arrival of the light sources, acceleration, angular velocity, and magnetic fields experienced by Picospace on the X, Y, and Z axes. <br /> <br /> This study used Inertial Measurement Unit (IMU) GY-80 sensor. It consists of accelerometer, magnetometer, and, gyrometer integrated in a single module. The LDR sensor (Light Dependent Resistor) is used as a substitute for the sun-tracker sensor and serves to detect the angle of the arrival of the LED light coming towards Picospace to be used as yaw attitude data of the system. The IMU sensor data readings are filtered with digital filters, a Complementary Filter is also used for the sensor data merging. The reading value of the LDR sensor is smoothed using an analog, Sallen-Key Low-Pass Filter. The purpose of the above filters is to reduce the effect of noise on sensor readings. <br /> <br /> The output of LDR sensor is converted into digital signal using ADC (Analog to Digital Converter) ADS1115. A Raspberry Pi 3 module is used to process the GY-80 sensor data readout and ADC1115 ADC output. <br /> <br /> The results of the system test show that the AHRS system has been able to detect the angular position of Picospace in the range -180 ° - 180 ° for yaw, and -30 ° - 30 ° for roll and pitch using IMU sensors. The system can also detect the direction of the incident angle of LED light within the range of -180 ° - 180°. <br /> <p align="justify">