Development of Control Algorithm and Fabrication of Attitude Determination and Control System for NanoSatellites

This paper explores the field of Satellite control systems. Inertial measurement units and sun sensors are two examples of the advanced sensor technologies that the proposed ADCS uses to accurately determine attitude[1]. Proportional-integral-derivative (PID) controllers and adaptive control techniques are used in a robust control system to combat external disturbances. This hybrid strategy improves the system's ability to adapt to the changing space environment and maximizes performance under a range of operating situations. Also, the Kalman filter was incorporated to filter out the drift of the sensors in the IMU. Fault-tolerant methods are also incorporated into the system to guarantee autonomous and dependable operation, which is essential for the Nanosatellites' longer mission life. The system's ability to achieve accurate attitude control at a low cost in a sustainable way is highlighted in the abstract as a means of enhancing the overall success of NanoSatellite missions. By precisely addressing the particular difficulties posed by NanoSatellite platforms, this ADCS design marks substantial progress in the area.