Angular microacceleration simulation for a satellite at very low Earth orbit

M. Yu. Ovchinnikov^a, Y. V. Mashtakov^a, D. S. Roldugin^a, S. S. Tkachev^a, D. S. Ivanov^a, V. Ya. Gecha^b, I. Yu. Pugach<sup>b

a</sup> Keldysh Institute of Applied Mathematics of RAS
^b VNIIEM Corporation

Abstract: 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.

Keywords: extremely low Earth orbit, magnetic attitude control, microaccelerations.

Received: 17.02.2025
Revised: 09.04.2025
Accepted: 28.04.2025

DOI: 10.20948/mm-2025-06-04