Design and simulation of a Radar System for tracking of objects in Low Earth Orbit

The proliferation of objects in Earth's orbit has surged since the launch of the first artificial satellite in 1957, posing significant threats to space security, safety, and long-term sustainability. As of November 1, 2022, the US Space Surveillance Network (SSN) tracks over 22,000 objects, with more than 90% being rocket bodies and debris. However, this covers just around 5% of the risk posed by potentially damaging collisions [8]. The European Space Agency estimates that roughly 900,000 objects sized between 1 and 10 cm are currently untracked [13]. To address this growing challenge, it is imperative to develop ground-based radar systems capable of detecting and tracking resident LEO objects down to 2 cm in diameter. For this reason, precise measurements are essential for extracting Keplerian elements used in orbit propagation. A single radar detection provides limited information, including the position vector and range ratio, which can introduce errors. Orbit determination requires the computation of all 6 Keplerian elements. One potential solution involves utilizing a pair of independent radars, consisting of cylindrical parabolic reflector fed by linear phased array. Each radar points in different directions from the same location, providing the range and the two angular positions of the object. This configuration allows the orbit to intersect both radar fields of view, providing 8 independent information (three-dimensional position and radial velocity for field of view) at least. These data not only facilitate orbit determination but also enhance its accuracy. This study emphasizes the optimization of beam inclination as a means to achieve the highest possible accuracy for orbit determination, making it a focal point of this thesis. In the initial phase, a basic two-dimensional model of the trajectory is constructed, and its outcomes and constraints are thoroughly examined. Subsequently, this two-dimensional model forms the foundation for the creation of an advanced three-dimensional trajectory model. This enhanced model enables the incorporation of additional variables regarding to the trajectory of potential objects, expanding the scope of analysis. After completing the preliminary design of radar parameters, we proceed to simulate various scenarios. These simulations consider both existing debris and satellite populations in Low Earth Orbit (LEO) to evaluate the radar's tracking performance