Trajectory Analysis and Optimization of Hesperides Mission

A challenging problem from a technological viewpoint is to send spacecraft at distance of about 600 au the Sun, comparable with that Sun’s gravitational focus (that is, general relativistic focusing light rays, whose minimum solar obtained when rays are assumed graze surface), and reach it in time interval on order human working lifetime. suitably oriented telescope would be theoretically able observe exoplanets tens years far away possibly discover new life forms. The transfer trajectory this mission rather complex requires close selection suitable propulsion system, which must provide probe necessary energy cruise velocity greater than 10 au/year. An effective outline these concepts given by Hesperides mission, originally proposed Matloff 2014. interesting aspect proposal combination nuclear electric system classical sail jointly exploited escape velocity. However, analysis reported very simplified essentially concentrated rough estimate required 600au. Starting baseline proposal, including vehicle mass distribution, aim work give detailed an optimal framework. In particular, calculated indirect methods parametric made highlight impact main design parameters total flight time. simulations show substantial reduction compared original study.