تعیین مدار ماهواره‌ با تلفیق دینامیک مداری و الگوریتم ژنتیک بر اساس نقاطی از خط سیر زمینی: یک رویکرد غیرفعال و مستقل

In an era marked by increasing space object congestion and the challenge of tracking uncooperative or passive satellites, the development of independent and cost-effective orbit determination methods is essential. This paper presents a novel and operational methodology that integrates classical orbital dynamics with a genetic optimization algorithm to extract the six classical orbital parameters of a satellite using only the geographical coordinates of a limited number of its ground track points. The proposed method is entirely passive, eliminating reliance on active navigation systems like GPS or external databases such as TLE (Two-Line Element) sets. Implementation in MATLAB and evaluation on two simulated scenarios (a standard orbit and a polar orbit) demonstrated that with only ten observational points, the average relative error of the orbital parameters was reduced to less than 0.7% for the standard orbit and approximately 1% for the polar orbit. The results indicate the high capability of the genetic algorithm in converging to the optimal solution and its robustness against outlier data. This method serves as an efficient complementary solution for space situational awareness, identification of unknown satellites, and tracking of large space debris.