Poincaré Filter for Trajectory Design in Multi-body Regime

Abstract

The Poincaré map and filter with an optimization algorithm for trajectory design in a multi-body regime is presented. The algorithm is capable of designing groups of trajectories that abide by the predetermined mission and spacecraft parameters. The algorithm is demonstrated by designing Weak stability boundary trajectories to the Earth-Moon periodic orbits about L1 and L2 and trajectories to Sun-Earth L4 Lagrange point's short period trajectories with spacecraft equipped with hybrid propulsion system using restricted threeand four-body problem formulation. Proposed Poincaré map analysis with filter is compared with the conventional Poincaré map analysis to demonstrate its improvement in both restricted body problem and the full ephemeris model.