MODELING THE DYNAMICS OF A SPACECRAFT DURING THE ATMOSPHERIC PHASE OF DEORBITING

Abstract

This study examines the modeling of the dynamics of an Earth remote-sensing spacecraft during the atmospheric phase of deorbiting. The research is based on the numerical solution of a system of differential equations describing the motion of the spacecraft within the dense layers of the Earth’s atmosphere. The calculations employ the International Standard Atmosphere, with initial parameters corresponding to a scenario in which the spacecraft begins its descent from an altitude of 100 km. The variations in velocity, altitude, flight angle, and horizontal range were determined, enabling the derivation of characteristic dependencies that describe the spacecraft’s behavior during passive atmospheric entry. The generated plots illustrate the key features of aerodynamic deceleration and the formation of the descent trajectory.

The obtained results make it possible to evaluate the deorbiting parameters of an Earth observation spacecraft, to estimate potential impact zones, and to use the data in the development of analytical and training tools. The analysis can be applied to end-of-life planning for remote-sensing satellites and can support the development of national methodologies for spacecraft deorbiting.