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dc.contributor.authorLian, Yijun
dc.contributor.authorGómez Muntané, Gerard
dc.contributor.authorMasdemont Soler, Josep
dc.contributor.authorTang, Guojian
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament de Matemàtica Aplicada I
dc.date.accessioned2014-07-09T11:19:18Z
dc.date.created2014-10-01
dc.date.issued2014-10-01
dc.identifier.citationLian, Yijun. [et al.]. Station-keeping of real Earth-Moon libration point orbits using discrete-time sliding mode control. "Communications in nonlinear science and numerical simulation", 01 Octubre 2014, vol. 19, núm. 10, p. 3792-3807.
dc.identifier.issn1007-5704
dc.identifier.urihttp://hdl.handle.net/2117/23453
dc.description.abstractIn this work, station-keeping of real Earth–Moon libration point orbits is studied using discrete-time sliding mode control (DSMC). For comparison, a discrete linear quadratic regulator (DLQR) controller is also considered. The libration orbits are termed “real” in the sense that they are obtained in a complete Solar System model, taking into account all the gravitational forces of the planets, the Moon, and the Sun. This is a key point for any station-keeping study, that the use of far from real orbits as nominal ones increases unnecessarily the station-keeping cost. The resulting controlled system, linearised with respect to some nominal orbit, takes a discrete-time form suitable for applying impulsive maneuvers. The DSMC controller is designed by the reaching law with the parameters chosen in an adaptive way. A method for designing the sliding surface is proposed. In order to assess and compare the performance of the two controllers, simulations are done for six libration point orbits around the L2L2 point (three halo orbits and three Lissajous ones) during a time span of 10 years. Several practical constraints are also considered in the simulations. Extensive Monte Carlo results show that the proposed DSMC approach is able to maintain the spacecraft within a close vicinity of the nominal orbits with a maneuver cost less than 2 m/s per year, and it outperforms the DLQR approach in terms of the position controllability. Some comparison with previous results obtained by other authors with different procedures is also given.
dc.format.extent16 p.
dc.language.isoeng
dc.rightsAttribution-NonCommercial-NoDerivs 3.0 Spain
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/3.0/es/
dc.subjectÀrees temàtiques de la UPC::Matemàtiques i estadística::Matemàtica aplicada a les ciències
dc.subject.lcshCelestial mechanics
dc.subject.otherStation-keeping
dc.subject.otherLibration point orbit
dc.subject.otherSiding mode control
dc.subject.otherLQR
dc.subject.otherDiscrete-time
dc.subject.otherEarth-Moon system
dc.subject.otherCONTROL-SYSTEMS
dc.subject.otherHALO ORBIT
dc.titleStation-keeping of real Earth-Moon libration point orbits using discrete-time sliding mode control
dc.typeArticle
dc.subject.lemacMecànica celest
dc.contributor.groupUniversitat Politècnica de Catalunya. EGSA - Equacions Diferencials, Geometria, Sistemes Dinàmics i de Control, i Aplicacions
dc.identifier.doi10.1016/j.cnsns.2014.03.026
dc.description.peerreviewedPeer Reviewed
dc.relation.publisherversionhttp://www.sciencedirect.com/science/article/pii/S100757041400152X
dc.rights.accessRestricted access - publisher's policy
local.identifier.drac14935069
dc.description.versionPostprint (published version)
dc.date.lift10000-01-01
local.citation.authorLian, Yijun.; Gómez Muntané, G.; Masdemont, J.J.; Tang, Guojian
local.citation.publicationNameCommunications in nonlinear science and numerical simulation
local.citation.volume19
local.citation.number10
local.citation.startingPage3792
local.citation.endingPage3807


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Attribution-NonCommercial-NoDerivs 3.0 Spain
Except where otherwise noted, content on this work is licensed under a Creative Commons license : Attribution-NonCommercial-NoDerivs 3.0 Spain