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Abstract:

This study addresses the problem of trajectory design for interplanetary missions utilizing electric propulsion (EP). A methodology is proposed for constructing, analyzing, and approximating the solution manifold of the energy-optimal rendezvous problem. Symbolic regression is employed as the approximation technique. The application of the proposed methodology is demonstrated on the manifold of energy-optimal solutions within the framework of a planar circular model of celestial body motion. It is shown that a manifold of non-coplanar transfers between elliptical orbits can be derived via linear transformations of control parameters. Key transfer characteristics are approximated, including flight duration, initial synodic phase, the objective function value, and optimal control parameters. Based on the identified properties of the manifold and the derived approximations, an algorithm is proposed for generating an initial guess for low-thrust interplanetary transfers (based on a PhD dissertation)