Performance analysis of sun sensors for satellite systems

This work is mainly proposed for servo stabilization of satellite along 1-axis. The satellite is 2-U cube sat. Attitude determination and control system (ADCS) is the most important part of any spacecraft. It measures and controls the motion of satellite and provides the necessary pointing accuracy to the antenna communication mode. ADCS depends on the sensor section. Various sensors are sun sensor, gyroscope and magnetometer. It is used for controlling the satellite´s angular rotation and also to prevent high spin rates that may damage the satellite structure or decrease its lifetime due to developed stresses. This paper describes the performance analysis of sun sensors. A sun sensor is a scientific instrument used to measure the orientation of the satellite with respect to sun and protect the sensitive equipment from sun´s ray and interferences. SIMULINK model and real time simulation model of sun sensor based stabilization of satellite model is discussed. Servo motor (360° continuous rotation) is used as an actuator along 1-axis. The sun sensor used is BH-1750. It is inexpensive and very small in size, thus it can be easily mounted on satellite solar panel. A prototype satellite model is developed and it is controlled by servo motor according to light intensity value sensed by sun sensor.