NMPC-based guidance and control for autonomous high-thrust non-coplanar LEO-GEO missions

This paper presents a novel Nonlinear Model Predictive Control strategy for autonomous guidance and control in high-thrust quasi-impulsive maneuvers. A sparse-in-time thrust behavior is promoted within the performance index. Sparsity and bang-bang behavior are indeed important features in view of the propellant consumption reduction. The guidance and control algorithm takes advantage of the so-called Modified Equinoctial Orbital Elements, which allow a reduction of potential numerical singularities with respect to the standard Keplerian elements. As case study, a non-coplanar Low Earth Orbit - Geostationary Orbit transfer mission is presented. In this case study, we show the effectiveness of the proposed strategy, compared to other approaches derived from classical astrodynamics.