Akademik Veri Yönetim Sistemi
23. National Astronomical Congress 2024 (UAK-2024), İstanbul, Türkiye, 2 - 06 Eylül 2024, ss.119
As a result of the solution of Newton's Equation, which consists of second-order homogeneous differential equations that form the basis of celestial mechanics, we obtain six integral constants. These integral constants correspond to the Keplerian orbit elements. Gravity-dependent and independent perturbing effects disrupt the homogeneity of Newton's Equation, causing the Keplerian orbit elements to change temporally. These perturbations are modeled as combinations of polynomial and trigonometric functions according to a reference epoch. The main purpose of this study is to show theoretically and practically how these disturbances are modeled in different (short and long-arc) orbit determination methods.