Initial Orbit Determination of Space Object Using Space-Based Optical Observations

An algorithm for initial orbit determination of space object using two short arcs from space-based optical observations is implemented and its feasibility is tested by simulation. The concept of attributable is introduced to represent the information in a short arc of observations. Using the attributables of two short arcs, angular-momentum and eccentricity-vector conservation equations of two-body problem are established to compute the initial orbit. Multiple solutions of these equations are obtained by variable transformation. A penalty function is constructed to select the optimal solution. Simulation results show that the algorithm can successfully compute the initial orbit with certain accuracy.