Evaluation of a liquid crystal based polarization modulator for a space mission thermal environment

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dc.citation.journalTitleSENSORS AND ACTUATORS A-PHYSICALeng
dc.contributor.authorSilva-López M.
dc.contributor.authorBastide L.
dc.contributor.authorRestrepo R.
dc.contributor.authorGarcía Parejo P.
dc.contributor.authorÁlvarez-Herrero A.
dc.contributor.departmentUniversidad EAFIT. Departamento de Ciencias Básicasspa
dc.contributor.researchgroupÓptica Aplicadaspa
dc.date.accessioned2021-04-12T14:18:43Z
dc.date.available2021-04-12T14:18:43Z
dc.date.issued2017-10-15
dc.description.abstractThe Multi Element Telescope for Imaging and Spectroscopy (METIS) is one of the remote sensing instruments to be onboard the future NASA/ESA Solar Orbiter mission. The science nominal mission orbit will take the spacecraft from 0.28 to 0.95 astronomical units from the Sun, setting challenging and variable thermal conditions to its payload. METIS is an inverted-occultation coronagraph that will image the solar corona in the visible and UV wavelength range. In the visible light path a Polarization Modulation Package (PMP) performs a polarimetric analysis of the incoming solar light. This PMP is based on liquid crystal variable retarders (LCVR) and works under a temporal modulation scheme. The LCVRs behavior has a dependence on temperature and, as a consequence, it is critical to guarantee the PMP performance in the mission thermal environment. Key system specifications are the optical quality and the optical retardance homogeneity. Moreover, the thermally induced elastic deformations of the mechanical mounts and the LCVRs shall not produce any performance degradation. A suitable thermal control is hence required to maintain the system within its allowed limits at any time. The PMP shall also be able to reach specific set-points with the power budget allocated. Consequently, and in order to verify the PMP thermal design, we have experimentally reproduced the expected thermal flight environment. Specifically, a thermal vacuum cycle test campaign is run at the different mission operational conditions. The purpose is both to check the stability of the thermal conditions and to study the optical quality evolution/degradation. Within this test transmitted wavefront measurements and functional verification tests have been carried out. To do that we adapted an optical interrogation scheme, based on a phase shifting interferometric technique, that allows for inspection of the PMP optical aperture. Finally, measurements obtained at nonoperational temperature conditions are also shown. These results demonstrate that the device meets the specifications required to perform its operational role in the space mission environment. (C) 2017 The. Authors. Published by Elsevier B.V.eng
dc.identifierhttps://eafit.fundanetsuite.com/Publicaciones/ProdCientif/PublicacionFrw.aspx?id=7520
dc.identifier.doi10.1016/j.sna.2017.09.033
dc.identifier.issn09244247
dc.identifier.otherWOS;000415777900028
dc.identifier.otherSCOPUS;2-s2.0-85029878924
dc.identifier.urihttp://hdl.handle.net/10784/27996
dc.languageeng
dc.language.isoengeng
dc.publisherElsevier B.V.
dc.relation.urihttps://www.scopus.com/inward/record.uri?eid=2-s2.0-85029878924&doi=10.1016%2fj.sna.2017.09.033&partnerID=40&md5=7221f42e230c1b2ca158a1048d6e0611
dc.rightshttps://v2.sherpa.ac.uk/id/publication/issn/0924-4247
dc.sourceSENSORS AND ACTUATORS A-PHYSICAL
dc.subject.keywordLiquid crystaleng
dc.subject.keywordThermal analysiseng
dc.subject.keywordWavefront measurementeng
dc.subject.keywordInterferometryeng
dc.subject.keywordOptical metrologyeng
dc.subject.keywordSpace missioneng
dc.titleEvaluation of a liquid crystal based polarization modulator for a space mission thermal environmenteng
dc.typeinfo:eu-repo/semantics/articleeng
dc.typearticleeng
dc.typeinfo:eu-repo/semantics/publishedVersioneng
dc.typepublishedVersioneng
dc.type.localArtículospa

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