Persona: Arruego, Ignacio
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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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Publicación Restringido Proton monitor las dos torres: First Intercomparison of In-Orbit Results(Institute of Electrical and Electronics Engineers, 2012-03-09) Jiménez Martín, Juan José; Oter, J. M.; Apéstigue, Víctor; Hernando, Carlos; Ibarmia, S.; Hajdas, W.; Sanchez Péramo, J.; Álvarez, Maite; Arruego, Ignacio; Guerrero, H.; Instituto Nacional de Técnica Aeroespacial (INTA)A new proton monitor on board NANOSAT-1B-Las Dos Torres (translated: The Two Towers)-and its preliminary results after two years in orbit and its intercomparison to a RadFET and to trapped proton models are presented. This satellite was fully developed by INTA (National Institute of Aerospace Technology, Spain) and was launched on July 29, 2009. The instrument includes two stacks of radiation-sensing elements: the "dark" and "light" towers. The displacement damage was measured, both through the increase of a photodiode dark current ("dark tower") and the decrease of the photocurrent signal in a photodiode optically linked to light emitting diodes ("light tower"). The instrument was also designed to monitor the ionization current of the photodiodes and the variations in the proton flux in the South Atlantic Anomaly.Publicación Acceso Abierto COTS-Based Wireless Magnetic Sensor for Small Satellites(Institute of Electrical and Electronics Engineers, 2010-05-06) Díaz Michelena, Marina; Arruego, Ignacio; Oter, J. M.; Guerrero, H.We report on the utilization of a commercial off-the-shelf (COTS) magnetic sensor for the mission NANOSAT-01 and the set of tests that have been developed to up-screen it. The magnetic sensor head is a Wheatstone bridge formed by four anisotropic magnetoresistances (AMR). AMR sensors are an adequate choice for medium- to high-sensitivity (~3 mV/V/G) and resolution (~ 3 ¿G) requirements, mostly due to their low weight and volume that are so interesting for the aerospace industry. The whole system installed in NANOSAT-01 is formed by two biaxial sensors with two redundant PCBs (printed circuit boards) of RAD-HARD proximity electronics, which conditions the AMR output signal, measure the temperature, and resets the AMR. This magnetic sensor belongs to the attitude control system (ACS) of the satellite.Publicación Acceso Abierto Drying of the Martian mesosphere during aphelion induced by lower temperatures(Springer Nature, 2024-11-20) Toledo, D.; Rannou, P.; Apéstigue, Víctor; Rodríguez Veloso, Raúl; Rodríguez Manfredi, J. A.; Arruego, Ignacio; Martínez, Germán M.; Tamppari, L. K.; Munguira, A.; Lorenz, Ralph; Stcherbinine, Aurélien; Montmessin, F.; Sánchez Lavega, Agustín; Patel, P.; Smith, Michael D.; Lemmon, M. T.; Vicente Retortillo, Álvaro; Newman, C. E.; Viúdez Moreiras, Daniel; Hueso, R.; Bertrand, T.; Pla García, J.; Yela González, Margarita; De la Torre Juárez, M.; Ministerio de Ciencia e Innovación (MICINN); Jet Propulsion Laboratory (JPL); National Aeronautics and Space Administration (NASA); Gobierno Vasco; Agencia Estatal de Investigación (AEI); Unidad de Excelencia Científica María de Maeztu Instituto de Astrofísica de Cantabria, MDM-2017-0765The formation of water ice clouds or hazes on Mars imposes substantial limitations on the vertical transport of water into the middle-upper atmosphere, impacting the planet’s hydrogen loss. Recent observations made by the Mars Environmental Dynamics Analyzer instrument onboard Mars 2020 Perseverance rover have shown a marked decline in water ice abundance within the mesosphere (above 35-40 km) when Mars is near its aphelion (near the northern summer solstice), notably occurring during solar longitudes (Ls) between Ls 70∘ and 80∘. Orbital observations around the same latitudes indicate that temperatures between ~ 30-40 km reach a minimum during the same period. Using cloud microphysics simulations, we demonstrate that this decrease in temperature effectively increases the amount of water cold-trapped at those altitudes, confining water ice condensation to lower altitudes. Similarly, the reinforcement of the cold trap induced by the lower temperatures results in significant reductions in the water vapor mixing ratio above 35–40 km, explaining the confinement of water vapor observed around aphelion from orbiters.Publicación Acceso Abierto Dust Devil Frequency of Occurrence and Radiative Effects at Jezero Crater, Mars, as Measured by MEDA Radiation and Dust Sensor (RDS)(GU Advancing Earth and Space Science, 2023-01-17) Toledo, D.; Apéstigue, Víctor; Arruego, Ignacio; Lemmon, M. T.; Gómez Martín, L.; Montoro, F.; Hueso, R.; Newman, C. E.; Smith, Michael D.; Viúdez Moreiras, Daniel; Martínez, Germán M.; Vicente Retortillo, Álvaro; Sánchez Lavega, Agustín; De la Torre Juárez, M.; Rodríguez Manfredi, J. A.; Carrasco, I.; Yela González, Margarita; Jiménez Martín, Juan José; García-Menéndez, Elisa; Navarro López, Sara; Gómez Elvira, J.; Harri, Ari-Matti; Polkko, J.; Hieta, M.; Genzer, María; Murdoch, N.; Sebastián, E.; Martínez, Germán M.; Agencia Estatal de Investigación (AEI); Ministerio de Ciencia e Innovación (MICINN); Ministerio de Economía y Competitividad (MINECO); NASA Jet Propulsion Laboratory (JPL); National Aeronautics and Space Administration (NASA); Gobierno VascoThe Mars Environmental Dynamics Analyzer, onboard the Perseverance rover, is a meteorological station that is operating on Mars and includes, among other sensors, the radiometer Radiation and Dust Sensor (RDS). From RDS irradiance observations, a total of 374 dust devils (DDs) were detected for the first 365 sols of the mission (Ls = 6°–182°), which along with wind and pressure measurements, we estimated a DD frequency of formation at Jezero between 1.3 and 3.4 DD km−2 sol−1 (increasing as we move from spring into summer). This frequency is found to be smaller than that estimated at the Spirit or Pathfinder landing sites but much greater than that derived at InSight landing site. The maximum in DD frequency occurs between 12:00 and 13:00 local true solar time, which is when the convective heat flux and lower planetary boundary layer IR heating are both predicted to peak in Jezero crater. DD diameter, minimum height, and trajectory were studied showing (a) an average diameter of 29 m (or a median of 25 m) and a maximum and minimum diameter of 132 ± 63.4 and 5.6 ± 5.5 m; (b) an average minimum DD height of 231 m and a maximum minimum-height of 872 m; and (c) the DD migration direction is in agreement with wind measurements. For all the cases, DDs decreased the UV irradiance, while at visible or near-IR wavelengths both increases and decreases were observed. Contrary to the frequency of formation, these results indicate similar DD characteristics in average for the studied period.Publicación Restringido Measurement of dust optical depth using the solar irradiance sensor (SIS) onboard the ExoMars 2016 EDM(Elsevier, 2017-01-20) Toledo, D.; Arruego, Ignacio; Apéstigue, Víctor; Jiménez Martín, Juan José; Gómez Martín, L.; Yela González, Margarita; Rannou, P.; Pommereau, J. P.; Instituto Nacional de Técnica Aeroespacial (INTA); Ministerio de Economía y Competitividad (MINECO)"The solar irradiance sensor (SIS) was included in the DREAMS package onboard the ExoMars 2016 Entry Descent and Landing Demonstrator Module, and has been selected in the METED meteorological station onboard the ExoMars 2020 Lander. This instrument is designed to measure at different time intervals the scattered flux or the sum of direct flux and scattered flux in UVA (315-400 nm) and NIR (700-1100 nm) bands. For SIS'16, these measurements are performed by a total of 3 sensors per band placed at the faces of a truncated tetrahedron with face inclination angles of 60. The principal goal of SIS'16 design is to perform measurements of the dust opacity in UVA and NIR wavelengths ranges, crucial parameters in the understanding of the Martian dust cycle. The retrieval procedure is based on the use of radiative transfer simulations to reproduce SIS observations acquired during daytime as a function of dust opacity. Based on different sensitivity analysis, the retrieval procedure also requires to include as free parameters (1) the, dust effective radius; (2) the dust effective variance; and (3) the imaginary part of the refractive index of dust particles in UVA band. We found that the imaginary part of the refractive index of dust particles does not have a big impact on NIR signal, and hence we can kept constant this parameter in the retrieval of dust opacity at this channel. In addition to dust opacity measurements, this instrument is also capable to detect and characterize clouds by looking at the time variation of the color index (CI), defined as the ratio between the observations in NIR and UVA channels, during daytime or twilight. By simulating CI signals with a radiative transfer model, the cloud opacity and cloud altitude (only during twilight) can be retrieved. Here the different retrieval procedures that are used to analyze SIS measurements, as well as the results obtained in different sensitivity analysis, are presented and discussed."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 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.Publicación Restringido A Sol–Gel based magneto-optical device for the NANOSAT space mission(Springer Link, 2009-03-31) Zayat, M.; Pardo, R.; Rosa, G.; Del Real, R. P.; Díaz Michelena, Marina; Arruego, Ignacio; Guerrero, H.; Levy, D.On December 2004, the Spanish Space Agency INTA (Instituto Nacional de Técnica Aeroespacial) launched the first nanosatellite called NANOSAT (Fig. 1) on board an European rocket Ariane 5, from the French Guyana. The satellite consists of a hexagonal device of <19 kg of weight with a diameter of about 50 cm, which describes a LEO orbit of 655 km of altitude. The main objective of the satellite is to probe the operation and performance of micro- and nanotechnologies in space environment. One of the scientific experiments implemented on board was the Sol–Gel based magnetic nanosensor.Publicación Restringido Calibration OGSEs for multichannel radiometers for Mars atmosphere studies(Springer Link, 2018-02-01) Jiménez Martín, Juan José; Álvarez Ríos, F. J.; González Guerrero, M.; Apéstigue, Víctor; Martín, I.; Fernández Marín, Juan Manuel; Fernán, A. A.; Arruego, Ignacio; Instituto Nacional de Técnica Aeroespacial (INTA); Ministerio de Economía y Competitividad (MINECO)This work describes several Optical Ground Support Equipment (OGSEs) developed by INTA (Spanish Institute of Aerospace Technology—Instituto Nacional de Técnica Aeroespacial) for the calibration and characterization of their self-manufactured multichannel radiometers (solar irradiance sensors—SIS) developed for working on the surface of Mars and studying the atmosphere of that planet. Nowadays, INTA is developing two SIS for the ESA ExoMars 2020 and for the JPL/NASA Mars 2020 missions. These calibration OGSEs have been improved since the first model in 2011 developed for Mars MetNet Precursor mission. This work describes the currently used OGSE. Calibration tests provide an objective evidence of the SIS performance, allowing the conversion of the electrical sensor output into accurate physical measurements (irradiance) with uncertainty bounds. Calibration results of the SIS on board of the Dust characterisation, Risk assessment, and Environment Analyzer on the Martian Surface (DREAMS) on board the ExoMars 2016 Schiaparelli module (EDM—entry and descent module) are also presented, as well as their error propagation. Theoretical precision and accuracy of the instrument are determined by these results. Two types of OGSE are used as a function of the pursued aim: calibration OGSEs and Optical Fast Verification (OFV) GSE. Calibration OGSEs consist of three setups which characterize with the highest possible accuracy, the responsivity, the angular response and the thermal behavior; OFV OGSE verify that the performance of the sensor is close to nominal after every environmental and qualification test. Results show that the accuracy of the calibrated sensors is a function of the accuracy of the optical detectors and of the light conditions. For normal direct incidence and diffuse light, the accuracy is in the same order of uncertainty as that of the reference cell used for fixing the irradiance, which is about 1%.Publicación Restringido Techniques to verify the sampling system and flow characteristics of the sensor MicroMED for the ExoMars 2022 Mission(Elsevier, 2021-08-21) Cozzolino, F.; Franzese, G.; Mongelluzzo, G.; Molfese, C.; Esposito, F.; Cosimo Ruggeri, A.; Porto, C.; Silvestro, S.; Popa, C. I.; Mennella, V.; Scaccabarozzi, D.; Saggin, B.; Ortega Rico, A. M.; Arruego, Ignacio; de Mingo Martín, José Ramón; Santiuste, Nuria; Brienza, D.; Cortecchia, F.; Instituto Nacional de Técnica Aeroespacial (INTA); Agenzia Spaziale Italiana (ASI); Istituto Nazionale di Astrofisica (INAF)Suspended dust has a prominent role in Martian climatology. Several significant dust related phenomena can be observed at various scales, starting from global dust storms to local dust devils, which have important effects such as the increase of troposphere temperature, the modification of the wind regime and the localized motion of sand at the surface. These phenomena depend on dust grain characteristics such as the size distribution or the chemical and bulk composition. Currently, we do not have direct measurement of the dust properties; the only available information in this regard are derived from spectrometric measurements, optical depth, and albedo coming from instruments aboard satellites and in-situ. Herein, we describe the tests performed on the optical particle counter named MicroMED, designed and built to perform the first ever direct in-situ measurement of suspended dust grains in the Martian atmosphere close to the surface. MicroMED is a dust particle size analyzer which was selected to join the Dust Complex payload aboard the ESA/Roscosmos ExoMars 2022 mission. It has the capability to suck in dust that is suspended in atmosphere and to measure the sizes of single grain. The sensor sucks in the dust grains using a sampling system, guides the grains through ducts and concentrates them in an area illuminated by laser. Detecting the intensity of the light scattered by the grains during the crossing through the illuminated area, it is possible to determinate the size of grain. Here we present the innovative techniques in order to verify the performances in terms of dust suction efficiency of the MicroMED Flight Model, using a prototype called MM1.Publicación Restringido Magnetic giant magnetoresistance commercial off the shelf for space applications(AIP Publishing, 2008-02-13) Díaz Michelena, Marina; Oelschlägel, W.; Arruego, Ignacio; Del Real, R. P.; Mateos, J. A. D.; Merayo, J. M.The increase of complexity and miniaturizing level of Aerospace platforms make use of commercial off the shelf (COTS) components constitute a plausible alternative to the use of military or rad-tolerant components. In this work, giant magnetoresistance commercial sensors are studied to be used as COTS, the next missions to be launched in the framework of the Spanish National Space Program: OPTOS and SEOSAT. This technology of magnetic sensors is interesting due to their high operating range up to 2mT and the high temperature dynamic range from −50 up to 150°C. However, in contrast, it presents high hysteresis and nonlinearity, temperature dependence, and poor repeatability. To improve the hysteretic, nonlinear and nonrepetitive behavior, a method consisting of a combination of reset and biasing has been designed and implemented for the ±75𝜇T linear region centered around 300–375𝜇T biasing field.
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