Study, simulation, design and manufacturing of attitude determination and control system for mini-satellite system in low earth orbit

Abstract

The objective of this thesis is to investigate the complete Study, simulation, design and fabricate of Attitude Determination and Control Systems (ADCS) in Earth-orbiting satellites specifically for the Low Earth Orbit(LEO). First part of the thesis focuses on the experimental determination of geomagnetic fields and methodologies, providing a solution to determine the orbit’s magnetic field in reference to the subsatellite point of the earth giving a new dimension to the research. ADCS is critical for maintaining a satellite's orientation relative to reference points such as Earth, the Sun, or other celestial bodies, allowing critical operations such as high-resolution imaging, precise data collection, and stable communication links. The research highlights the importance of attitude control systems (ADCS) in modern space missions as well as the difficulties associated with achieving accuracy and reliability in attitude control. Magnetometers, Helmholtz cages, and inertial measurement units (IMUs) are among the components and technologies examined in this study.