In the satellite attitude determination and control subsystem, the main objective is to mitigate environmental disturbances to achieve and maintain the desired attitude. The design of this subsystem depends not only on the satellite’s physical properties but also on two key factors: disturbance torques induced by the space environment and required performance criteria such as pointing accuracy and stability. For CubeSats, where physical characteristics are largely predefined, understanding environmental disturbances requires analyzing the impact of orbital variations.This study investigates the primary disturbance torques, the factors influencing them, and possible mitigation approaches. The governing equations for each disturbance component are presented, followed by a description of the simulation methodology. To improve computational accuracy, high-fidelity atmospheric models are employed, given the significant role of atmospheric drag torque at low altitudes. The results show that atmospheric modeling significantly affects disturbance characterization in low Earth orbit. The analysis considers altitudes from 200 to 1200 km, including both circular and elliptical orbits.