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dc.creatorFernandez-Rico, German
dc.creatorAlvarez-Copano, Miguel
dc.creatorDeutsch, Werner
dc.creatorGandorfer, Achim
dc.creatorRamanath, Sandeep
dc.creatorStaub, Jan
dc.creatorBambach, Patrick
dc.creatorTorralbo, Ignacio
dc.date.accessioned2018-07-08T01:45:52Z
dc.date.available2018-07-08T01:45:52Z
dc.date.issued2018-07-08
dc.identifier.otherICES_2018_292
dc.identifier.urihttp://hdl.handle.net/2346/74235
dc.descriptionICES203: Thermal Testing
dc.descriptionThe 48th International Conference on Environmental Systems was held in Albuquerque, New Mexico, USA on 08 July 2018 through 12 July 2018.
dc.descriptionGerman Fernandez-Rico, Max-Planck-Institut für Sonnensystemforschung
dc.descriptionMiguel Alvarez-Copano, Max-Planck-Institut für Sonnensystemforschung
dc.descriptionWerner Deutsch, Max-Planck-Institut für Sonnensystemforschung
dc.descriptionAchim Gandorfer, Max-Planck-Institut für Sonnensystemforschung
dc.descriptionSandeep Ramanath, Max-Planck-Institut für Sonnensystemforschung
dc.descriptionJan Staub, Max-Planck-Institut für Sonnensystemforschung
dc.descriptionPatrick Bambach, Max-Planck-Institut für Sonnensystemforschung
dc.descriptionIgnacio Torralbo, Universidad Politécnica de Madrid
dc.description.abstractPHI (Polarimetric and Helioseismic Imager) is one of the remote sensing instruments which will fly on board of ESA Solar Orbiter mission. It consists of two entrance filters, an optics unit, an electronics unit and an external harness that links both units. Prior to the instrument delivery to the Spacecraft prime contractor (Airbus UK), PHI was subjected to a thermal vacuum cycling test, which is described in this paper. The test had a threefold objective: the acceptance test of the optics and electronics unit, the thermal model correlation of the optics unit, and the spectral calibration of the instrument. The PHI optics unit is an internally mounted insulated unit, thermally coupled to the spacecraft only through dedicated interfaces and optical apertures towards the Sun, whereas the electronics unit is strongly coupled to the spacecraft through its base. These characteristics required the control of up to 12 interfaces, including the thermal vacuum chamber shroud. For the spectral calibration, it was needed to feed the instrument with natural sunlight. This was done by means of a coelostat that drives the sunlight through the building inside the thermal vacuum chamber. Due to geometrical distribution of baseplate and viewports in the chamber, it was necessary to mount the whole PHI instrument on a high stand 0.5 m above the thermal vacuum chamber baseplate, which was used as a general heat sink for the controlled interfaces. Finally, the entrance filters were monitored through infrared cameras, which could see inside the chamber through dedicated Zinc-Selenide viewports and a mobile stainless steel flat mirror.en_US
dc.language.isoengen_US
dc.publisher48th International Conference on Environmental Systemsen_US
dc.subjectPolarimetric and Helioseismic Imager
dc.subjectSolar Orbiter
dc.subjectThermal vacuum test
dc.subjectThermal balance test
dc.titleThermal vacuum and balance test of the ESA Solar Orbiter Instrument PHIen_US
dc.typePresentationen_US


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