A numerical simulation of satellite dynamics in a near-circular orbit at an altitude of 250 km is performed. The satellite is equipped with a magnetic attitude control system that complements its aerodynamic stabilization properties. A continuous-thrust engine is utilized to mitigate the effects of atmospheric drag. A brief description of the models used is provided. The magnitudes of microaccelerations are simulated and analyzed with respect to various satellite parameters, the models employed, and the algorithms implemented.
Ovchinnikov et al. (Wed,) studied this question.