Simulation-Driven ADCS for Sun-Pointing 1U Nano-Satellite: Design and Comprehensive Analysis

The Sun-Pointing attitude mode is essential for Low Earth Orbit (LEO) CubeSats, particularly those relying on solar panels for energy generation. This study presents the development of an Attitude Determination and Control System (ADCS) for the Sun-Pointing mode of a 1U nanosatellite, incorporating environment modeling, controller design, and the implementation of a closed-loop output feedback control system within a custom 3D simulation environment. A satellite health monitoring simulator has been created, enabling users to configure various sensor setups, integrate additional sensors seamlessly, and visualize reference, measured, estimated, and controlled states along with pointing error metrics, enhancing performance evaluation and optimization. The ADCS is further validated using STK software, demonstrating precise Sun tracking during orbital operations. Covering the complete process from satellite deployment to mission execution, this study provides a comprehensive framework for understanding and designing satellite attitude control systems, serving as a valuable resource for education, research, and advancing future satellite operational modes by integrating theoretical concepts with practical simulations.