Persona: Reina Aranda, Manuel
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Instituto Nacional de Técnica Aeroespacial
El Instituto Nacional de Técnica Aeroespacial es el Organismo Público de Investigación (OPI) dependiente del Ministerio de Defensa. Además de realizar actividades de investigación científica y de desarrollo de sistemas y prototipos en su ámbito de conocimiento, presta servicios tecnológicos a empresas, universidades e instituciones.
El INTA está especializado en la investigación y el desarrollo tecnológico, de carácter dual, en los ámbitos de la Aeronáutica, Espacio, Hidrodinámica, Seguridad y Defensa.
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Reina Aranda
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Manuel
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Publicación Restringido Liquid-crystal variable retarders for aerospace polarimetry applications(OSA (The Optical Society) Publishing, 2007-01-25) López Heredero, Raquel; Uribe Patarroyo, Néstor; Belenguer Dávila, T.; Ramos, G.; Sánchez, A.; Reina Aranda, Manuel; Martínez Pillet, V.; Álvarez-Herrrero, Alberto; 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.Publicación Restringido Low stiffness thermal straps for cryogenic applications(SPIE Digital Library, 2024-08-26) Torres, J.; Martínez, M.; Fernández Sánchez, Miguel; Díaz Robisco, Ángel; Martín, S.; Sánchez, A.; Reina Aranda, ManuelIn cryogenics, working together with cryocoolers, the thermal straps are a critical thermal element, since they thermally link the instrument with the cold source. In optical elements that work at cryogenic temperatures, the thermal path, and therefore the straps, must isolate them from the vibrations of the cryocoolers. Consequently, its stiffness is a characteristic to consider in the design. But, in the case of optical focal plane arrays, working at very low temperatures such as 50 mK, it can be resonant with the low frequency range of the cryocoolers, and its dissipation can break the superconducting state of the sensors, the basis of its functioning. It is therefore an undesired thermal effect derived from structural behavior. Design limitations impose the need for straps where stiffness is just as important as its conductance. The stiffness value needed is much lower than the one found in commercial straps. Therefore, this work highlights the design, and characterization tests of different strap prototypes in order to achieve the necessary resistivity and thermal conductivity for low cryogenic temperatures. The thermal straps were initially designed for the Cryostat facility for 2K Core Calibration (C2CC) a ground equipment for the ATHENA project (Advanced Telescope for High - ENergy Astrophysics, ESA).Publicación Restringido Heat switch to reduce cooldown times for a ground cryostat(Spie Digital Library, 2024-08-26) Fernández Sánchez, Miguel; Bastide, L. ; Sánchez, A.; Reina Aranda, ManuelA passive heat switch is an element used to conduce heat flow at high temperatures (from 300 to 100 K) and to insulate at low temperatures (< 10 K). Its goal is to accelerate the cool down transient phase and reduce the waiting time from the cryostat closure until the temperature stabilization required to perform the tests. The ground cryostat (C2CC - Cryostat for 2 K core Calibration) being developed at INTA for cryogenic tests and future missions includes a 300 K vessel, intermediate shields at 40 and 4 K (temperatures achieved with Pulse-Tube crycoolers) and final 2 K shield. The heat switch is made up with a conductive core consisting of graphite (pyrolytic) embedded at its two extremity in a copper fitting to provide a high coupling between the interface and the graphite core. The graphite material is chosen because the thermal conductivity reduction with temperature, being at 1 K 10000 times lower than at 300 K. As a consequence, when the cool down starts, higher heat loads can be removed from the 2 K shield by the 4 K shield coolers through the heat switch. While the stages are being cooled, this heat removal decreases little by little, and when the operating temperatures are reached, the heat switch barely conduces heat, so the heat loads from the 4 K shield on the Joule-Thomson cooler are so low that they don’t affect the nominal behaviour of the cryostat. At INTA, a heat switch was produced and tested, in order to obtain a thermal conductivity curve of the material through experimental means, and the total conductance of the thermal switch. This characterization should enable to validate this design, and conclude on the introduction of this element in the thermal design of the cryostat.Publicación 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-Herrrero, Alberto; Díaz Michelena, Marina; Martín, I.; Tamayo, R.; Reina Aranda, Manuel; 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.Publicación 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, Raquel; 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 Aranda, Manuel; 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.Publicación 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-Herrrero, Alberto; 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.; López Heredero, Raquel; Herranz, M.; Jerónimo, J. M.; Laguna, H.; Meller, R.; Menéndez, M.; Morales, R.; Orozco Suárez, D.; Ramos, G.; Reina Aranda, Manuel; Ramos, J. L.; Rodríguez, P.; Sánchez, A.; Uribe Patarroyo, Néstor; 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 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.Publicación Acceso Abierto PT410 Cold Head dynamic characterization(IOP Science, 2024-07-23) Pérez Barrio, Sandra; Díaz Robisco, Ángel; Morata Barrado, Pablo; Fernández Sánchez, Miguel; Reina Aranda, Manuel; García Martín, P.In the design of cryostats that use cryocoolers, the characterization of the cryocooler is crucial for vibration-sensitive applications. This study focuses on the PT410 pulse tube cryocooler from Cryomech, using modal and microvibration testing. Modal testing examined the natural frequencies and vibration modes of the cold head. Microvibration testing determined the interface forces caused by the cryocooler’s operation on the mechanical mounting interface and the accelerations induced on the thermal interface of the cold stages. The first bending modes of the cryocooler were identified through modal testing. Forces were directly measured using triaxial load cells, and accelerations of the cryocooler stages were recorded with accelerometers. The characterization was performed on a test bench designed for precise measurements. The cold head of the cryocooler is supplied by a helium flow pulse, which introduces vibration. Consequently, an additional support was added for the supply line elements. This study characterizes the dynamic response and mechanical stability of the PT410 cold head based on measured data and testing results. These results are essential for the designing and developing of cryogenic systems where controlling vibrations is critical.Publicación 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-Herrrero, Alberto; Belenguer Dávila, T.; Pastor, C.; González, L.; López Heredero, Raquel; Ramos, G.; Reina Aranda, Manuel; 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; 0000-0003-4343-6632; 0000-0002-6297-0681; 0000-0002-3387-026X; 0000-0002-6210-9648; 0000-0002-4944-5823; 0000-0001-7764-6895; 0000-0003-1661-0594; 0000-0001-9631-9558; 0000-0002-1225-4177In 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.Publicación 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-Herrrero, Alberto; Belenguer Dávila, T.; López Heredero, Raquel; Menéndez, M.; Ramos, Gonzalo; Reina Aranda, Manuel; 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.Publicación 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, David; Belenguer Dávila, T.; Blanco, J.; Figueroa, I.; García, G.; González, L.; López Heredero, Raquel; Herrada, F. J.; Laviada Hernández, C.; March, M.; Pastor, C.; Reina Aranda, Manuel; 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.
