Hybrid multi-objective orbit-raising with operational constraints

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dc.contributor.author Morante González, David
dc.contributor.author Sanjurjo Rivo, Manuel
dc.contributor.author Soler Arnedo, Manuel Fernando
dc.contributor.author Sánchez Pérez, José Manuel
dc.date.accessioned 2021-03-09T12:23:16Z
dc.date.available 2022-10-01T23:00:06Z
dc.date.issued 2020-10
dc.identifier.bibliographicCitation Morante, D., Sanjurjo-Rivo, M., Soler, M., Sánchez-Pérez, J. M. (2020). Hybrid multi-objective orbit-raising optimization with operational constraints. Acta Astronautica, 175, 447–461.
dc.identifier.issn 0094-5765
dc.identifier.uri http://hdl.handle.net/10016/32089
dc.description.abstract The optimal design of orbit raising trajectories is formulated within a multi-objective hybrid optimal control framework. The spacecraft can be equipped with chemical, electric or combined chemical-electric propulsion systems. The model incorporates realistic effects of the space environment and complex operational constraints. An automated solution strategy, based on two sequential steps, is proposed for this problem. In the first step, operational constraints are not enforced and the control law of the electric engine is parameterized by a Lyapunov function. A heuristic global search algorithm selects the propulsion system and optimizes the guidance law. Approximate Pareto-optimal solutions are obtained trading off propellant mass, time of flight and solar-cell degradation. In the second step, candidate solutions are deemed as initial guesses to solve the nonlinear programming problem resulting from direct transcription of the operationally constrained problem. The proposed approach is applied to two transfer scenarios to the geostationary orbit. Results show the effectiveness of the methodology to generate not only rapid performance estimates for preliminary trade studies, but also accurate calculations for the detailed design. Additionally, it is identified that the application of operational restrictions causes minor penalties in the objective function.
dc.format.extent 15
dc.language.iso eng
dc.publisher Elsevier
dc.rights © 2020 Elsevier
dc.rights Atribución-NoComercial-SinDerivadas 3.0 España
dc.rights.uri http://creativecommons.org/licenses/by-nc-nd/3.0/es/
dc.subject.other Hybrid optimal control
dc.subject.other Combined chemical-electric orbit raising
dc.title Hybrid multi-objective orbit-raising with operational constraints
dc.type article
dc.subject.eciencia Aeronáutica
dc.identifier.doi https://doi.org/10.1016/j.actaastro.2020.05.022
dc.rights.accessRights openAccess
dc.relation.projectID Gobierno de España. TRA2014-58413-C2-2-R
dc.type.version acceptedVersion
dc.identifier.publicationfirstpage 447
dc.identifier.publicationlastpage 461
dc.identifier.publicationtitle Acta Astronautica
dc.identifier.publicationvolume 175
dc.identifier.uxxi AR/0000026352
dc.contributor.funder Ministerio de Economía y Competitividad (España)
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