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EnglishPropellant consumption minimization is a key factor in space missions, as it strongly affects the duration of any mission. Nowadays, delta-V guidance strategies are obtained by means of classical ground based open loop methods, while academic research has mainly focused on autonomous low-thrust strategies. However, classical methods return instantaneous impulsive thrust actions that are not always feasible in practice, due to the technical limitations of real propulsion systems. In this paper, a novel Nonlinear Model Predictive Control framework for autonomous guidance and control with high-thrust quasi-impulsive maneuvers is presented. The internal prediction model is based on the so-called Modified Equinoctial Orbital Elements, which allow us to overcome relevant singularities given by the standard Keplerian elements. Different NMPC cost functions are compared in order to have a sparse thrust profile, minimize at the same time the propellant consumption and the tracking error with respect to the target orbit. In particular, it is shown how non-quadratic norms could achieve better performances. Finally, an Earth Observation mission, employing different NMPC functionals, is used as a benchmark and the results are compared with the ones coming from the classical astrodynamics solutions.
A Sparse Nonlinear Model Predictive Control for Autonomous Space Missions / Pagone, Michele; Boggio, Mattia; Novara, Carlo; Massotti, Luca; Vidano, Simone. - ELETTRONICO. - (2020). ((Intervento presentato al convegno 71st International Astronautical Congress (IAC) — IAC CyberSpace Edition nel 12-14 October 2020.
| Titolo: | A Sparse Nonlinear Model Predictive Control for Autonomous Space Missions | |
| Autori: | ||
| Data di pubblicazione: | 2020 | |
| Serie: | ||
| Abstract: | Propellant consumption minimization is a key factor in space missions, as it strongly affects the... duration of any mission. Nowadays, delta-V guidance strategies are obtained by means of classical ground based open loop methods, while academic research has mainly focused on autonomous low-thrust strategies. However, classical methods return instantaneous impulsive thrust actions that are not always feasible in practice, due to the technical limitations of real propulsion systems. In this paper, a novel Nonlinear Model Predictive Control framework for autonomous guidance and control with high-thrust quasi-impulsive maneuvers is presented. The internal prediction model is based on the so-called Modified Equinoctial Orbital Elements, which allow us to overcome relevant singularities given by the standard Keplerian elements. Different NMPC cost functions are compared in order to have a sparse thrust profile, minimize at the same time the propellant consumption and the tracking error with respect to the target orbit. In particular, it is shown how non-quadratic norms could achieve better performances. Finally, an Earth Observation mission, employing different NMPC functionals, is used as a benchmark and the results are compared with the ones coming from the classical astrodynamics solutions. | |
| Appare nelle tipologie: | 4.1 Contributo in Atti di convegno |
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http://hdl.handle.net/11583/2846364
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