Design and Analysis of Reaction Wheel for Nanosatellite ADCS System

Attitude Determination and Control Systems (ADCS) play a critical role in nanosatellite missions, enabling precise orientation control essential for tasks such as Earth observation, communication, and scientific experimentation. Given the size, weight, and power limitations inherent to nanosatellite platforms, the development of compact, efficient, and reliable components, including reaction wheels, presents a significant challenge in ADCS design. This work focuses on the design, dimensioning, modal and quasi-static analysis, and prototyping of a reaction wheel intended for integration into an educational nanosatellite platform (PEDAGO-SAT). The mechanical design was developed using SolidWorks, with the flywheel dimensioned based on the required inertia constraints to ensure effective attitude control, while optimizing both mass and structural efficiency. Integration of the flywheel, motor, supporting structure, and associated electronics was carried out with particular attention to spatial constraints and power consumption. Finite Element Analysis (FEA) using ANSYS software was conducted to perform modal and quasi-static simulations, ensuring that the structure can withstand the mechanical stresses encountered during launch. The results confirm the structural integrity and stiffness of the proposed reaction wheel design, validating its suitability for the harsh environmental conditions of space missions.