The Imaging Magnetograph eXperiment (IMaX) for the Sunrise Balloon-Borne Solar Observatory

Pillet, V. Martínez; Iniesta, J. C. del Toro; Alvarez-Herrero, A.; Domingo, V.; Bonet, J. A.; Fernández, L. González; López-Jiménez, A.; Sempere, Carmen Pastor; Gasent-Blesa, J. L.; Mellado, Paula; Piqueras, J.; Aparicio, Beatriz; Jiménez, M. Balaguer; Ballesteros, E.; Belenguer, T.; Rubio, L. R. Bellot; Berkefeld, Thomas; Collados, M.; Deutsch, W.; Feller, A.; Girela, F.; Grauf, B.; Heredero, R. L.; Herranz, M.; Jeronimo, J. M.; Laguna, H.; Meller, R.; Menéndez, M.; Morales, R.; Suárez, D. Orozco; Ramos, G.; Reina, M.; Ramos, José Luis Martínez; Rodríguez, P.; Sánchez, Antonio; Uribe-Patarroyo, Néstor; Barthol, P.; Gandorfer, A.; Knoelker, M.; Schmidt, Wolfgang; Solanki, S. K.; Domínguez, Santiago Vargas

doi:10.1007/s11207-010-9644-y

Cited by 229 publications

(30 citation statements)

References 32 publications

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“…IMaX was developed by a Spanish consortium led by the Instituto de Astrofísica de Canarias, La Laguna (Tenerife), in cooperation with the Instituto de Astrofísica de Andalucía, Granada, the Instituto Nacional de Tecnicas Aeroespaciales, Madrid, and the Grupo de Astronomia y Ciencias del Espacio, Valencia. The instrument is described by Martínez Pillet et al (2010).…”

Section: Imaging Magnetograph Experiment: Imaxmentioning

confidence: 99%

The Sunrise Mission

et al. 2010

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The first science flight of the balloon-borne Sunrise telescope took place in June 2009 from ESRANGE (near Kiruna/Sweden) to Somerset Island in northern Canada. We describe the scientific aims and mission concept of the project and give an overview and a description of the various hardware components: the 1-m main telescope with its postfocus science instruments (the UV filter imager SuFI and the imaging vector magnetograph IMaX) and support instruments (image stabilizing and light distribution system ISLiD and correlating wavefront sensor CWS), the optomechanical support structure and the instrument mounting concept, the gondola structure and the power, pointing, and telemetry systems, and the general electronics architecture. We also explain the optimization of the structural and thermal design of the complete payload. The preparations for the science flight are described, including AIV and ground calibration of the instruments. The course of events during the science flight is outlined, up to the recovery activities. Finally, the in-flight performance of the instrumentation is discussed.

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Section: Imaging Magnetograph Experiment: Imaxmentioning

confidence: 99%

The Sunrise Mission

et al. 2010

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“…The polarimetric analysis is performed by one polarization modulation package (PMP) [2] in each of the telescopes. The modulation scheme is the same as the one used in the IMaX instrument of the Sunrise mission [3]. In addition to these two main units, the SO/PHI design also includes two Heat Rejection Entrance Windows (HREW) one for each telescope.…”

Section: Introductionmentioning

confidence: 99%

Optical performance of the SO/PHI full disk telescope due to temperature gradients effect on the heat rejection entrance window

Garranzo

Zuluaga-Ramírez

Barandiarán

et al. 2017

International Conference on Space Optics — ICSO 2014

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The Polarimetric Helioseismic Imager for Solar Orbiter (SO/PHI) is an instrument on board in the Solar Orbiter mission. The Full Disk Telescope (FDT) will have the capability of providing images of the solar disk in all orbital faces with an image quality diffraction-limited. The Heat Rejection Entrance Window (HREW) is the first optical element of the instrument. Its function is to protect the instrument by filtering most of the Solar Spectrum radiation. The HREW consists of two parallel-plane plates made from Suprasil and each surface has a coating with a different function: an UV shield coating, a low pass band filter coating, a high pass band filter coating and an IR shield coating, respectively. The temperature gradient on the HREW during the mission produces a distortion of the transmitted wave-front due to the dependence of the refractive index with the temperature (thermo-optic effect) mainly. The purpose of this work is to determine the capability of the PHI/FDT refocusing system to compensate this distortion. A thermal gradient profile has been considered for each surface of the plates and a thermal-elastic analysis has been done by Finite Element Analysis to determine the deformation of the optical elements. The Optical Path Difference (OPD) between the incident and transmitted wavefronts has been calculated as a function of the ray tracing and the thermo-optic effect on the optical properties of Suprasil (at the work wavelength of PHI) by means of mathematical algorithms based on the 3D Snell Law. The resultant wavefronts have been introduced in the optical design of the FDT to evaluate the performance degradation of the image at the scientific focal plane and to estimate the capability of the PHI refocusing system for maintaining the image quality diffraction-limited. The analysis has been carried out considering two different situations: thermal gradients due to on axis attitude of the instrument and thermal gradients due to 1º off pointing attitude. The effect over the boresight at the instrument focal plane has also been analyzed. The results show that the effect of the FDT HREW thermal gradients on the FDT performance can be optically corrected. The influence of the thermal gradients on the system is also presented.

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Section: Introductionmentioning

confidence: 99%

Ion irradiation effects on lithium niobate etalons for tunable spectral filters

Garranzo

Ibarmia

Alvarez-Herrero

et al. 2017

International Conference on Space Optics — ICSO 2014

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Solar Orbiter is a mission dedicated to solar and heliospheric physics. It was selected as the first mediumclass mission of ESA's Cosmic Vision 2015-2025 Programme. Solar Orbiter will be used to examine how the Sun creates and controls the heliosphere, the vast bubble of charged particles blown by the solar wind into the interstellar medium. One of the scientific payload elements of Solar Orbiter is the Polarimetric and Helioseismic Imager (PHI). The PHI instrument consists of two telescopes, a High Resolution Telescope (HRT) that will image a fraction of the solar disk at a resolution reaching ~150 km at perihelion, and a Full Disk Telescope (FDT) to image the full solar disk during all phases of the orbit. PHI is a diffraction limited, wavelength tunable, quasi-monochromatic, polarisation sensitive imager. These capabilities are needed to infer the magnetic field and line-of-sight (LOS) velocity of the region targeted by the spacecraft. For the spectral analysis, PHI will use an order-sorting filter to isolate a bandpass of the order of 100 mÅ. The FilterGraph (FG) contains an etalon in single pass configuration as tunable spectral filter located inside a temperature stabilized oven. This filter will be made by means of a z-cut LiNbO3 crystal (about 300 microns thick) and multilayer coatings including a conductive one in order to apply a high voltage (up to 5 kV) and induce the required electric field to tune the filter.Solar Orbiter observing mission around the Sun will expose the PHI instrument to extreme radiation conditions, mainly dominated by solar high-energy particles released during severe solar events (protons with energies typically ranging from few keV up to several GeV) and the continuous isotropic background flux of galactic cosmic rays (heavy ions, from Z=1 to Z=92). The main concerns are whether the cumulated radiation damage can degrade the functionality of the filter or, in the worst case, the impact of a single highly ionizing particle, coupled with the HV field, could trigger a dielectric breakdown in the Lithium Niobate.In this paper we present the electro-optical results obtained when exposing a set of LN samples and a lowquality full size etalon to different radiation conditions. In a first irradiation campaign, performed at the Centre for Micro Analysis of Materials (CMAM-Madrid) facilities, we were mainly focused on the long-term degradation effects with a series of high flux (10 9 cm -2 s -1 ) proton tests at an energy of 10 MeV. In order to study the possibility of a single ion breakdown, a second campaign was carried out, at the Texas A&M University (TAMU), exposing Lithium Niobate to high LET ion species ( 78 Kr, 40 Ar, 129 Xe, 197 Au) accelerated to the GeV energy range to penetrate or even pass through the entire Lithium Niobate thickness.

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The Imaging Magnetograph eXperiment (IMaX) for the Sunrise Balloon-Borne Solar Observatory

Cited by 229 publications

References 32 publications

The Sunrise Mission

The Sunrise Mission

Optical performance of the SO/PHI full disk telescope due to temperature gradients effect on the heat rejection entrance window

Ion irradiation effects on lithium niobate etalons for tunable spectral filters

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