Iterative Lambert’s Trajectory Optimization for Extrasolar Bodies Interception

Interception of extrasolar objects is one the major current astrophysical objectives since it allows gathering information on formation and composition other planetary systems. This paper develops a tool to design optimal orbits for interception these bodies considering effects different perturbation sources. The trajectory obtained by solving Lambert’s problem that gives required initial impulse. A numerical integration perturbed orbital model calculated. considers perturbations joint action gravitational potentials Solar System planets solar radiation pressure. These cause deviation in orbit prevents from taking place, so an iterative correction scheme estimated impulse presented, capable modifying achieving successful more realistic environment.