ASSESSMENT OF PASSIVE DEORBITING OF THE KAZAKH EARTH REMOTE SENSING SATELLITES KAZEOSAT-1 AND KAZEOSAT-2
DOI:
https://doi.org/10.37943/25KZEM7835Keywords:
deorbiting, spacecraft, Earth remote sensing, KazEOSat-1, KazEOSat-2, satellite, orbitAbstract
In this work, passive deorbiting of the Kazakh Earth remote sensing satellites KazEOSat-1 and KazEOSat-2, operating in sun-synchronous low Earth orbits and not equipped with onboard deorbiting systems, is investigated. The object of the study is the dynamics of their orbital motion and the processes of aerodynamic drag during the final stage of operation. Using numerical modeling, time-dependent variations of the main orbital elements were obtained, the rates of orbital altitude decay were estimated, and possible timelines for passive deorbiting were evaluated. In addition, a sensitivity analysis of the results to variations in aerodynamic parameters was performed. It was established that the differences in the orbital evolution of the KazEOSat-1 and KazEOSat-2 spacecraft are mainly determined by the combination of orbital altitude and ballistic coefficient. In particular, the lower orbital altitude and smaller ballistic coefficient of KazEOSat-2 lead to more intense aerodynamic drag and, consequently, to accelerated orbital decay. The orbital degradation of KazEOSat-1 occurs at a significantly slower rate. A distinctive feature of the presented results is their applicability to real operating spacecraft that are not equipped with deorbiting systems, as well as the consideration of uncertainties in aerodynamic characteristics, which made it possible to obtain well-grounded estimates of passive deorbiting timelines. The results of the study can be used in planning the end-of-life phase of Earth remote sensing spacecraft, in assessing the risks of non-compliance with international recommendations on orbital deorbiting timelines, and in substantiating the need for passive or active deorbiting systems in the development of future spacecraft of a similar type.
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