Examinando por Autor "Reina, M."

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Restringido
Detailed design of the imaging magnetograph experiment (IMaX): a visible imager magnetograph for the Sunrise mission
(SPIE Astronomical Telescopes Instrumentation, 2006-07-07) Álvarez Herrero, A.; Belenguer Dávila, T.; Pastor, C.; González, L.; López Heredero, R.; Ramos, G.; Reina, M.; Sánchez, A.; Villanueva, J.; Sabau, L.; Martínez Pillet, V.; Bonet Navarro, J. A.; Collados Vera, Manuel; Jochum, L.; Ballesteros, E.; Medina Trujillo, J. L.; Ruiz, C. B.; González, J. C.; Del Toro Iniesta, J. C.; López Jiménez, A. C.; Castillo Lorenzo, J.; Herranz, M.; Jerónimo, J. M.; Mellado, P.; Morales, R.; Rodríguez, J.; Domingo, V.; Gasent, J. L.; Rodríguez, P.; 0000-0003-0248-2771; 0000-0001-9228-3412; 0000-0003-4343-6632; 0000-0002-6297-0681; 0000-0002-3387-026X; 0000-0002-2197-8388; 0000-0002-6210-9648; 0000-0002-4944-5823; 0000-0001-7764-6895; 0000-0003-1661-0594; 0000-0001-9631-9558; 0000-0002-1225-4177
In this work, it is described the Imaging Magnetograph eXperiment, IMaX, one of the three postfocal instruments of the Sunrise mission. The Sunrise project consists on a stratospheric balloon with a 1 m aperture telescope, which will fly from the Antarctica within the NASA Long Duration Balloon Program. IMaX will provide vector magnetograms of the solar surface with a spatial resolution of 70 m. This data is relevant for understanding how the magnetic fields emerge in the solar surface, how they couple the photospheric base with the million degrees of temperature of the solar corona and which are the processes that are responsible of the generation of such an immense temperatures. To meet this goal IMaX should work as a high sensitivity polarimeter, high resolution spectrometer and a near diffraction limited imager. Liquid Crystal Variable Retarders will be used as polarization modulators taking advantage of the optical retardation induced by application of low electric fields and avoiding mechanical mechanisms. Therefore, the interest of these devices for aerospace applications is envisaged. The spectral resolution required will be achieved by using a LiNbO3 Fabry-Perot etalon in double pass configuration as spectral filter before the two CCDs detectors. As well phase-diversity techniques will be implemented in order to improve the image quality. Nowadays, IMaX project is in the detailed design phase before fabrication, integration, assembly and verification. This paper briefly describes the current status of the instrument and the technical solutions developed to fulfil the scientific requirements.
Restringido
Liquid-crystal variable retarders for aerospace polarimetry applications
(OSA (The Optical Society) Publishing, 2007-01-25) López Heredero, R.; Uribe Patarroyo, N.; Belenguer Dávila, T.; Ramos, G.; Sánchez, A.; Reina, M.; Martínez Pillet, V.; Álvarez Herrero, A.; Álvarez Herrero, A. [0000-0001-9228-3412]; López Heredero, R. [0000-0002-2197-8388]; Martínez Pillet, V. [0000-0001-7764-6895]
We present the optical effects of different tests that simulate the aerospace environment on the liquid-crystal variable retarders (LCVRs) used in the Imaging Magnetograph eXperiment postfocal instrument of the SUNRISE payload within the NASA Long Duration Balloon program. Analysis of the influence of vacuum, temperature, vibration, and gamma and ultraviolet radiation is performed by measuring the effects of these tests on the optical retardance, the response time, the wavefront distortion, and the transmittance, including some in situ measurements. Outgassing measurements of the different parts of the LCVRs are also shown. From the results obtained it can be concluded that these optical devices are suitable and seem to be excellent candidates for aerospace platforms.
Acceso Abierto
Mars environmental networks through the MarsConnect microprobes
(Europlanet, 2025-01-23) Arruego, Ignacio; Apéstigue, Víctor; Bastide, L.; Azcue, J.; Gonzalo Melchor, Alejandro; Martínez Oter, J.; Caballero, N.; Liaño, G.; Torres, J.; González Guerrero, M.; Serrano, F.; De Mingo, J. R.; Rivas, J.; Andrés Santiuste, N.; Carrasco, I.; Fernández, M.; Reina, M.; Ruiz Carrasco, J. R.; Poyatos Martínez, David; Scaccabarozzi, D.; Frövel, M.; De la Torre, M. A.; Martín, S.; Pedraza, R.
In the last 15 years the Payloads Department of INTA has developed a variety of compact sensors for different Mars exploration missions. This includes a magnetometer (72 g), a dust sensor (35 g; with UC3M, Spain) and a radiometer (114 g) for the MetNet penetrator [1]; a radiometer (25 g optical head, 56 g processor) for DREAMS (Schiaparelli) [2], [3]; a radiometer plus camera (1 kg) for MEDA on Perseverance [4], [5]; a 110 g dust sensor (with UC3M, Spain) [6] and a radiometer plus spectrometer (180 g) for the METEO package [7] on Kazachock lander (ExoMars’22) and a 0.5 kg nephelometer (with INAF and Politecnico di Milano, Italy) [8] for the Dust Complex on the same lander. Equally miniaturized sensors exist for the measurement of the most relevant environmental variables, such as radiative balance, air temperature, wind, humidity, pressure, dust saltation, electric field, etc. with enough flight heritage (or technology readiness level) on the same sensors’ suites on Perseverance and ExoMars, as well as Insight or Curiosity before [9]. In summary, a large portfolio of miniature sensors for environmental research is available at present. However, a qualitative leap on (in-situ) Mars climate science will only happen through the deployment of networks of environmental stations throughout large areas of the planet. Given the relevance of these measurement not only from a scientific point of view but also because of their importance for future human missions to Mars, this is an objective considered in several Mars exploration roadmaps such as ESA’s Terrae Novae 2030+ [10]. With this aim, we propose a microprobe named MarsConnect. It consists of a 10-12 kg probe with a rigid, deployable aeroshell/TPS and a 5-6 kg impactor/penetrator carrying up to 1 kg of environmental sensors. Many of these probes could be launched to Mars with a single carrier, to deploy meteorological networks. This works inherits different concepts from previous similar proposals, very specially MetNet and MiniPINS [11], but simplifying even more the EDL concept and reducing the mass, at the expense of an increased impact speed. The probe’s aeroshell is divided into a backshell and two halves of a frontshield that are opened in the low supersonic regime to drop the penetrator. This one is equipped with a drag-skirt that provides some braking and increases stability. The expected impact speed, highly dependent on the atmospheric density profile, entry conditions and landing altitude, ranges from less than 100 to 140 m/s. The whole system is designed to be compatible with a wide range of scenarios and landing sites and is sized to endure more than one Martian year operating on the planet’s surface.
Restringido
OSIRIS – The Scientific Camera System Onboard Rosetta
(Springer Link, 2007-01-12) Keller, H. U.; Barbieri, C.; Lamy, Philippe; Rickman, H.; Rodrigo, Rafael; Wenzel, K. P.; Sierks, H.; A´Hearn, M. F.; Angrilli, F.; Angulo, M.; Bailey, M. E.; Barthol, P.; Barucci, M. A.; Bertaux, J. L.; Bianchini, G.; Boit, J. L.; Brown, V.; Burns, J. A.; Büttner, I.; Castro, J. M.; Cremonese, G.; Curdt, W.; Da Deppo, V.; Debei, S.; De Cecco, M.; Dohlen, K.; Fornasier, S.; Fulle, M.; Germerott, D.; Gliem, F.; Guizzo, G. P.; Hviid, S. F.; Ip, W. H.; Jorda, L.; Koschny, D.; kramm, J. R.; Kührt, E.; Küppers, M.; Lara, L. M.; Llebaria, A.; López, A.; López Jiménez, A. C.; López Moreno, J. J.; Meller, R.; Michalik, H.; Díaz Michelena, Marina; Müller, R.; Naletto, G.; Origné, A.; Parzianello, G.; Pertile, M.; Quintana, C.; Ragazzoni, R.; Ramous, P.; Reiche, K. U.; Reina, M.; Rodríguez, J.; Rousset, G.; Sabau, L.; Sanz Andrés, Ángel; Sivan, J. P.; Stöckner, K.; Telljohann, U.; Thomas, N.; Timón, V.; Tomasch, G.; Wittrock, T.; Zaccariotto, M.
The Optical, Spectroscopic, and Infrared Remote Imaging System OSIRIS is the scientific camera system onboard the Rosetta spacecraft (Figure 1). The advanced high performance imaging system will be pivotal for the success of the Rosetta mission. OSIRIS will detect 67P/Churyumov-Gerasimenko from a distance of more than 106 km, characterise the comet shape and volume, its rotational state and find a suitable landing spot for Philae, the Rosetta lander. OSIRIS will observe the nucleus, its activity and surroundings down to a scale of ~2 cm px−1. The observations will begin well before the onset of cometary activity and will extend over months until the comet reaches perihelion. During the rendezvous episode of the Rosetta mission, OSIRIS will provide key information about the nature of cometary nuclei and reveal the physics of cometary activity that leads to the gas and dust coma. OSIRIS comprises a high resolution Narrow Angle Camera (NAC) unit and a Wide Angle Camera (WAC) unit accompanied by three electronics boxes. The NAC is designed to obtain high resolution images of the surface of comet 67P/Churyumov-Gerasimenko through 12 discrete filters over the wavelength range 250–1000 nm at an angular resolution of 18.6 μrad px−1. The WAC is optimised to provide images of the near-nucleus environment in 14 discrete filters at an angular resolution of 101 μrad px−1. The two units use identical shutter, filter wheel, front door, and detector systems. They are operated by a common Data Processing Unit. The OSIRIS instrument has a total mass of 35 kg and is provided by institutes from six European countries.
Acceso Abierto
OWLS: a ten-year history in optical wireless links for intra-satellite communications
(Institute of Electrical and Electronics Engineers 27(9): 1599-1611(2009), 2009-12-10) Arruego, Ignacio; Guerrero, H.; Rodríguez, Santiago; Martínez Oter, J.; Jiménez Martín, Juan José; Domínguez, J. A.; Martín-Ortega, Alberto; de Mingo Martín, José Ramón; Rivas, J.; Apéstigue, Víctor; Sánchez, J.; Iglesias, J.; Álvarez, M. T.; Gallego, P.; Azcue, J.; Ruiz de Galarreta, C.; Martín Vodopivec, B.; Álvarez Herrero, A.; Díaz Michelena, Marina; Martín, I.; Tamayo, R.; Reina, M.; Gutiérrez, M. J.; Sabau, L.; Torres, J.
The application of Optical Wireless Links to intra- Spacecraft communications (OWLS) is presented here. This work summarizes ten years of developments, ranging from basic optoelectronic parts and front-end electronics, to different inorbit demonstrations. Several wireless applications were carried out in representative environments at ground level, and on in-flight experiments. A completely wireless satellite will be launched at the beginning of 2010. The benefits of replacing standard data wires and connectors with wireless systems are: mass reduction, flexibility, and simplification of the Assembly, Integration and Tests phases (AIT). However, the Aerospace and Defense fields need high reliability solutions. The use of COTS (Commercial-Off-The- Shelf) parts in these fields require extensive analyses in order to attain full product assurance. The current commercial optical wireless technology needs a deep transformation in order to be fully applicable in the aforementioned fields. Finally, major breakthroughs for the implementation of optical wireless links in Space will not be possible until dedicated circuits such as mixed analog/digital ASICs are developed. Once these products become available, it will also be possible to extend optical wireless links to other applications, such as Unmanned Air and Underwater Vehicles (UAV and UUV). The steps taken by INTA to introduce Optical Wireless Links in the Space environment are presented in this paper.
Acceso Abierto
Radiation and Dust Sensor for Mars Environmental Dynamic Analyzer Onboard M2020 Rover
(Multidisciplinary Digital Publishing Institute (MDPI), 2022-04-10) Apéstigue, Víctor; Gonzalo Melchor, Alejandro; Jiménez Martín, Juan José; Boland, J.; Lemmon, M. T.; de Mingo Martín, José Ramón; García-Menéndez, Elisa; Rivas, J.; Azcue, J.; Bastide, L.; Andrés Santiuste, N.; Martínez Oter, J.; González Guerrero, M.; Martín-Ortega, Alberto; Toledo, D.; Álvarez Ríos, F. J.; Serrano, F.; Martín Vodopivec, B.; Manzano, Javier; López Heredero, R.; Carrasco, I.; Aparicio, S.; Carretero, Á.; MacDonald, D. R.; Moore, L. B.; Alcacera Gil, María Ángeles; Fernández Viguri, J. A.; Martín, I.; Yela González, Margarita; Álvarez, Maite; Manzano, Paula; Martín, J. A.; del Hoyo Gordillo, Juan Carlos; Reina, M.; Urquí, R.; Rodríguez Manfredi, J. A.; De la Torre Juárez, M.; Hernández, Christina; Córdoba, Elizabeth; Leiter, R.; Thompson, Art; Madsen, Soren N.; Smith, Michael D.; Viúdez Moreiras, Daniel; Saiz López, A.; Sánchez Lavega, Agustín; Gómez Martín, L.; Martínez, Germán M.; Gómez Elvira, J.; Arruego, Ignacio; Instituto Nacional de Técnica Aeroespacial (INTA); Comunidad de Madrid; Gobierno Vasco; Ministerio de Economía y Competitividad (MINECO); Agencia Estatal de Investigación (AEI); National Aeronautics and Space Administration (NASA)
The Radiation and Dust Sensor is one of six sensors of the Mars Environmental Dynamics Analyzer onboard the Perseverance rover from the Mars 2020 NASA mission. Its primary goal is to characterize the airbone dust in the Mars atmosphere, inferring its concentration, shape and optical properties. Thanks to its geometry, the sensor will be capable of studying dust-lifting processes with a high temporal resolution and high spatial coverage. Thanks to its multiwavelength design, it will characterize the solar spectrum from Mars’ surface. The present work describes the sensor design from the scientific and technical requirements, the qualification processes to demonstrate its endurance on Mars’ surface, the calibration activities to demonstrate its performance, and its validation campaign in a representative Mars analog. As a result of this process, we obtained a very compact sensor, fully digital, with a mass below 1 kg and exceptional power consumption and data budget features.
Acceso Abierto
The athena x-ray integral field unit: a consolidated design for the system requirement review of the preliminary definition phase
(Springer Link, 2022-08-30) Barret, Didier; Albouys, Vincent; Den Herder, Jan-Willem; Piro, Luigi; Cappi, Massimo; Huovelin, Juhani; Kelley, Richard; Mas-Hesse, J. Miguel; Paltani, Stéphane; Rauw, Gregor; Rozanska, Agata; Acero, Fabio; Vera Trallero, Isabel; Grosso, Nicolas; Varnière, Peggy; Genolet, Ludovic; Charles, Ivan; Miniutti, Giovanni; Ullom, Joel; Sato, Kosuke; Bulgarelli, Andrea; Laurent, Philippe; Adami, Christophe; Rigano, Manuela; Langer, Mathieu; Granat, Dolorès; Pinsard, Frederic; Schaye, Joop; Walmsley, Gavin; Woźniak, Grzegorz; Aicardi, Corinne; Perry, James; Dupourqué, Simon; Ledot, Aurélien; Fioretti, Valentina; Surace, Christian; Nicastro, Fabrizio; Sciortino, Salvatore; Jiménez, María; Jolly, Antoine; Bounab, Ayoub; Maussang, Irwin; Smith, Stephen; Clerc, Laurent; Lo Cicero, Ugo; Kiviranta, Mikko; Cavazzuti, Elisabetta; Roelfsema, Peter; Roig, Anton; Medinaceli Villegas, Eduardo; Lesrel, Jean; Boyce, Kevin; Dupieux, Michel; Durkin, Malcom; Argan, Andrea; Pascale, Ramon; Eckert, Dominique; Soucek, Jan; Kammoun, Elias; Bonny, Patrick; Yamaguchi, Hiroya; Auricchio, Natalia; Beaumont, Sophie; Ettori, Stefano; Cucchetti, Edoardo; Pointecouteau, Etienne; Akamatsu, Hiroki; Vidriales, María; Lotti, Simone; Calarco, Simona; Zuchniak, Monika; Merino Alonso, Pablo Eleazar; Kreykenbohm, Ingo; Wakeham, Nicholas; Soto Aguilar, Javier; Vink, Jacco; De Wit, Martin; Silva, Vitor; Kaastra, Jelle; Den Hartog, Roland; Taralli, Emanuele; Clerc, Nicolas; Coleiro, Alexis; Van Leeuwen, Bert-Joost; Guignard, Nicolas; Torrioli, Guido; Ubertini, Pietro; Bernard, Vivian; Miller, Jon; Eiriz, Valvanera; Boreux, Charles; Poyatos Martinez, David; Pratt, Gabriel W.; Molin, Alexeï; Minervini, Gabriele; Le Mer, Isabelle; De Vries, Cor; Yamasaki, Noriko; Goldwurm, Andrea; Coynel, Alexandre; Van Loon, Dennis; Dadina, Mauro; Prouvé, Thomas; Brachet, Frank; Porter, Frederick; Spizzi, Pierre; Jourdan, Thierry; Massonet, Didier; Lyautey, Bertrand; Sciortino, Luisa; Pinto, Ciro; Vibert, Laurent; Simionescu, Aurora; Boutelier, Martin; Roncarelli, Mauro; Julien, Sabine; González, Raoul; Maffei, Bruno; Todaro, Michela; Balado, A.; Ferrando, Philippe; Atienza, R.; Schwander, Denis; Millerioux, Jean-Pierre; Godet, Olivier; Sanisidro, Julien; Bancel, Florian; Vaccaro, Davide; Webb, Natalie; Camus, Thierry; Coriat, Mickael; Carron, Jérôme; Piconcelli, Enrico; Puccetti, Simonetta; Mitsuda, Kazuhisa; Mineo, Teresa; Jaubert, Jean; D'Ai, Antonino; Adam, Thomas; Frericks, Martin; Costantini, Elisa; Janiuk, Agnieszka; Cobo, Beatriz; Ghizzardi, Simona; Gatti, Flavio; Molendi, Silvano; Wise, Michael; Bandler, Simon; Torrejón, José Miguel; Kedziora, Bartosz; Dauser, Thomas; Prêle, Damien; Duband, Lionel; Terrier, Régis; Pajot, François; Daniel, Christophe; Ferrari Barusso, Lorenzo; Mot, Baptiste; Vodopivec, Boris Martin; Giovannini, Elisa; DeNigris, Natalie; Encinas Plaza, José Miguel; Van der Kuur, Jan; González, Manuel; Amato, Roberta; Geoffray, Hervé; Dercksen, Johannes; Pradines, Alice; Rollet, Bertrand; Dubbeldam, Luc; Terrasa, Guilhem; Alcacera Gil, María Ángeles; Maisonnave, Océane; DiPirro, Michael; Monestes, David; Laurenza, Monica; Boorman, Peter; Bozzo, Enrico; Capobianco, Vito; Parot, Yann; D'Andrea, Matteo; Korb, Andrew; Nagayoshi, Kenichiro; Roudil, Gilles; Doumayrou, Eric; Gao, Jian-Rong; Luminari, Alfredo; Khosropanah, Pourya; Gloaguen, Emilie; Branduardi Raymont, Graziella; Peille, Philippe; Gabici, Stefano; Eckart, Megan; Franssen, Philippe; Shinozaki, Keisuke; Gonzalo Melchor, Alejandro; Ptak, Andy; Chervenak, James; Michalski, Lea; Castellani, Florent; Cuttaia, Francesco; Thibert, Tanguy; Hieltjes, Paul; Hurtado, Adolfo Jesus; Fossecave, Hervé; Irwin, Kent; Adams, Joseph; Attard, Anthony; Etcheverry, Christophe; Rioland, Guillaume; Natalucci, Lorenzo; Finoguenov, Alexis; Jacquey, Christian; Barbera, Marco; Barcons, Xavier; Varisco , Salvatore; Mendez, Mariano; Ercolani, Eric; Fernández Sánchez, Miguel; Gastaldello, Fabio; Uslenghi, Michela; Angelinelli, Matteo; Jacques, Lionel; Villa, Fabrizio; Lorenz, Maximilian; Mesnager, Jean-Michel; Durand, Jean Louis; Sakai, Kazuhiro; Decourchelle, Anne; Martin, Sylvain; Berrocal, A.; Finkbeiner, Fred; Wilms, Joern; Reina, M.; Rudnicki, Tomasz; Doriese, William; Nazé, Yaël; Abdoelkariem, Shariefa; D'anca, Fabio; Gant, Florent; Van der Hulst, Paul; Mazzotta, Pasquale; Coeur-Joly, Odile; Añón Cancela, M.; Canourgues, Florent; Fiore, Fabrizio; Raulin, Desi; Noguès, Loïc; Hoogeveen, Ruud; Ravera, Laurent; Callanan, Paul; Cheatom, Oscar; André, Jérôme; Sordet, Michael; Brienza, Daniele; Duval, Jean-Marc; Corcione, Leonardo; Fiocchi, Maria Teresa; Pailot, Damien; Panessa, Francesca; Fioretti, Valentina; Van Weers, Henk; Anvar, Shebli; Parodi, Luigi; Petit, Pascal; De Plaa, Jelle; Kirsch, Christian; Macculi, Claudio; Volpe, Angela; Puccio, Elena; Gómez Elvira, J.; Bonnet, François; Marelli, Lorenzo; Murat, David; Audard, Marc; Jackson, Brian; Colonges, Stéphane; Korpela, Seppo; Webb, Natalie; Laudet, Philippe; Chiarello, Fabio; Ligori, Sebastiano; Montinaro, Nicola; Svoboda, Jiri; Bij de Vaate, Jan Geralt; Blin, Sylvie; Jonker, Peter; Bruijn, Marcel; Ceballos, Maria Teresa; Cardiel, Nicolás; Kilbourne, Caroline; Chaoul, Laurence; Gottardi, Luciano; Gros, Michel; Bonino, Donata; Skup, Konrad; Rodriguez, Louis; Fiorini, Mauro; Ardellier, Florence; Bellouard, Elise; Agencia Estatal de Investigación (AEI); Ministerio de Ciencia e Innovación (MICINN); Centre National D'Etudes Spatiales (CNES); Agenzia Spaziale Italiana (ASI); European Space Agency (ESA)
The Athena X-ray Integral Unit (X-IFU) is the high resolution X-ray spectrometer, studied since 2015 for flying in the mid-30s on the Athena space X-ray Observatory, a versatile observatory designed to address the Hot and Energetic Universe science theme, selected in November 2013 by the Survey Science Committee. Based on a large format array of Transition Edge Sensors (TES), it aims to provide spatially resolved X-ray spectroscopy, with a spectral resolution of 2.5 eV (up to 7 keV) over an hexagonal field of view of 5 arc minutes (equivalent diameter). The X-IFU entered its System Requirement Review (SRR) in June 2022, at about the same time when ESA called for an overall X-IFU redesign (including the X-IFU cryostat and the cooling chain), due to an unanticipated cost overrun of Athena. In this paper, after illustrating the breakthrough capabilities of the X-IFU, we describe the instrument as presented at its SRR, browsing through all the subsystems and associated requirements. We then show the instrument budgets, with a particular emphasis on the anticipated budgets of some of its key performance parameters. Finally we briefly discuss on the ongoing key technology demonstration activities, the calibration and the activities foreseen in the X-IFU Instrument Science Center, and touch on communication and outreach activities, the consortium organisation, and finally on the life cycle assessment of X-IFU aiming at minimising the environmental footprint, associated with the development of the instrument. Thanks to the studies conducted so far on X-IFU, it is expected that along the design-to-cost exercise requested by ESA, the X-IFU will maintain flagship capabilities in spatially resolved high resolution X-ray spectroscopy, enabling most of the original X-IFU related scientific objectives of the Athena mission to be retained.
Acceso Abierto
The Imaging Magnetograph eXperiment (IMaX) for the Sunrise Balloon-Borne Solar Observatory
(Springer Link, 2011-01-17) Martínez Pillet, V.; Del Toro Iniesta, J. C.; Álvarez Herrero, A.; Domingo, V.; Bonet Navarro, J. A.; González Fernández, C.; López Jiménez, A. C.; Pastor, C.; Gasent Blesa, J. L.; Mellado, P.; Piqueras, J.; Aparicio, B.; Balaguer, M.; Ballesteros, E.; Belenguer Dávila, T.; Bellot Rubio, L. R.; Berkefeld, T.; Collados Vera, Manuel; Deutsch, W.; Feller, A.; Girela, F.; Grauf, B.; Heredero, R. L.; Herranz, M.; Jerónimo, J. M.; Laguna, H.; Meller, R.; Menéndez, M.; Morales, R.; Orozco Suárez, D.; Ramos, G.; Reina, M.; Ramos, J. L.; Rodríguez, P.; Sánchez, A.; Uribe Patarroyo, N.; Barthol, P.; Gandorfer, A.; Knoelker, M.; Schmidt, Walter; Solanki, S. K.; Vargas Domínguez, S.; Ministerio de Ciencia e Innovación (MICINN); Deutsches Zentrum für Luft- und Raumfahrt (DLR); National Aeronautics and Space Administration (NASA); López Heredero, R. [0000-0002-2197-8388]; López Jiménez, A. [0000-0002-6297-0681]; Balaguer, M. [0000-0003-4738-7727]; Del Toro Iniesta, J. C. [0000-0002-3387-026X]; Reina Aranda, M. [0000-0003-0248-2771]; Álvarez Herrero, A. [0000-0001-9228-3412]; Herranz de la Revilla, M. L. [0000-0003-4343-6632]; Morales Muñoz, R. [0000-0003-1661-0594]; Pastor, C. [0000-0001-9631-9558]; Gasent Blesa, J. L. [0000-0002-1225-4177]; Collados, M. [0000-0002-6210-9648]; Jerónimo, J. M. [0000-0002-4944-5823]; Bellot Rubio, L. R. [0000-0001-8669-8857]; Martínez Pillet, V. [0000-0001-7764-6895]
The Imaging Magnetograph eXperiment (IMaX) is a spectropolarimeter built by four institutions in Spain that flew on board the Sunrise balloon-borne solar observatory in June 2009 for almost six days over the Arctic Circle. As a polarimeter, IMaX uses fast polarization modulation (based on the use of two liquid crystal retarders), real-time image accumulation, and dual-beam polarimetry to reach polarization sensitivities of 0.1%. As a spectrograph, the instrument uses a LiNbO3 etalon in double pass and a narrow band pre-filter to achieve a spectral resolution of 85 mÅ. IMaX uses the high-Zeeman-sensitive line of Fe I at 5250.2 Å and observes all four Stokes parameters at various points inside the spectral line. This allows vector magnetograms, Dopplergrams, and intensity frames to be produced that, after reconstruction, reach spatial resolutions in the 0.15 – 0.18 arcsec range over a 50×50 arcsec field of view. Time cadences vary between 10 and 33 s, although the shortest one only includes longitudinal polarimetry. The spectral line is sampled in various ways depending on the applied observing mode, from just two points inside the line to 11 of them. All observing modes include one extra wavelength point in the nearby continuum. Gauss equivalent sensitivities are 4 G for longitudinal fields and 80 G for transverse fields per wavelength sample. The line-of-sight velocities are estimated with statistical errors of the order of 5 – 40 m s−1. The design, calibration, and integration phases of the instrument, together with the implemented data reduction scheme, are described in some detail.
Restringido
The imaging magnetograph eXperiment for the SUNRISE balloon Antarctica project
(SPIE Astronomical Telescopes Instrumentation, 2004-10-12) Martínez Pillet, V.; Bonet Navarro, J. A.; Collados Vera, Manuel; Jochum, L.; Mathew, S.; Medina Trujillo, J. L.; Ruiz Cobo, B.; Del Toro Iniesta, J. C.; López Jiménez, A. C.; Castillo Lorenzo, J.; Herranz, M.; Jerónimo, J. M.; Mellado, P.; Morales, R.; Rodríguez, J.; Álvarez Herrero, A.; Belenguer Dávila, T.; López Heredero, R.; Menéndez, M.; Ramos, Gonzalo; Reina, M.; Pastor, C.; Sánchez, A.; Villanueva, J.; Domingo, V.; Gasent, J. L.; Rodríguez, P.; López Heredero, R. [0000-0002-2197-8388]; López Jiménez, A. [0000-0002-6297-0681]; Reina, M. [0000-0003-0248-2771]; Del Toro Iniesta, J. C. [0000-0002-3387-026X]; Álvarez Herrero, A. [0000-0001-9228-3412]; De la Revilla, M. L. [0000-0003-4343-6632]; Callados, M. [0000-0002-6210-9648]; Morales Muñoz, R. [0000-0003-1661-0594]; Rodríguez Gómez, J. [0000-0002-6757-5912]; Ruiz Cobo, B. [0000-0001-9550-6749]; Gasent Blesa, J. L. [0000-0002-1225-4177]; Jerónimo, J. M. [0000-0002-4944-5823]; Pastor, C. [0000-0001-9631-9558]
The SUNRISE balloon project is a high-resolution mission to study solar magnetic fields able to resolve the critical scale of 100 km in the solar photosphere, or about one photon mean free path. The Imaging Magnetograph eXperiment (IMaX) is one of the three instruments that will fly in the balloon and will receive light from the 1m aperture telescope of the mission. IMaX should take advantage of the 15 days of uninterrupted solar observations and the exceptional resolution to help clarifying our understanding of the small-scale magnetic concentrations that pervade the solar surface. For this, IMaX should act as a diffraction limited imager able to carry out spectroscopic analysis with resolutions in the 50.000-100.000 range and capable to perform polarization measurements. The solutions adopted by the project to achieve all these three demanding goals are explained in this article. They include the use of Liquid Crystal Variable Retarders for the polarization modulation, one LiNbO3 etalon in double pass and two modern CCD detectors that allow for the application of phase diversity techniques by slightly changing the focus of one of the CCDs.
Restringido
The MIRI cold telescope simulator
(SPIE Astronomical Telescopes Instrumentation, 2004-10-12) Colina, L.; Díaz, E.; Aricha, A.; Alcacera Gil, María Ángeles; Balado, A.; Barandiarán, J.; Barrado, D.; Belenguer Dávila, T.; Blanco, J.; Figueroa, I.; García, G.; González, L.; López Heredero, R.; Herrada, F. J.; Laviada Hernández, C.; March, M.; Pastor, C.; Reina, M.; Sánchez, A.; Barrado, D. [0000-0002-5971-9242]; López Heredero, R. [0000-0002-2197-8388]; Balado, A. [0000-0003-4268-2516]; Colina, L. [0000-0002-9090-4227]; Pastor, C. [0000-0001-9631-9558]
The MIRI Telescope Simulator (MTS) is part of the Optical Ground Support System (OGSE) for the verification and calibration phase of the James Webb Space Telescope (JWST) Mid-Infrared Instrument (MIRI). The MTS will simulate the optical characteristics of the JWST output beam in an environment similar to the flight conditions. The different functionalities of the MTS are briefly described and its current design, including the illumination and imaging subsystems, is presented.