Persona: Apéstigue, Víctor
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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 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.; 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-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 Generic Entry Probe Program (GEPP) – an international initiative promoting the development of European descent modules dedicated to the in situ exploration of giant planets(EGU European Geosciences Union, 2024-04-17) Ambrosi, R.; André, N.; Andrews, J.; Apéstigue, Víctor; Atkinson, D.; Arruego, Ignacio; Blanc, M.; Boithias, H.; Bolton, S.; Bousquet, P.; Canup, R.; Cavalié, T.; Freeman, A.; Faye, F.; Ferri, F.; Glein, C.; Guelhan, A.; Hartogh, P.; Loehle, S.; Hue, V.; Lebreton, J. P.; Lemaistre, S.; Mooij, E.; Pichon, T.; Pinaud, G.; Steuer, D.; Toledo Carrasco, D.; Rauer, H.; Vorbuger, A.; Wurz, P.The international consortium GEPP has been set to conceptualize probe designs with appropriate payloads that would remain within the typical budget allocated for ESA M-class missions (currently 500 M€). The aims of the consortium are i) to conceptualize a line of generic planetary entry probes that could be targeted to the giant planets with very few modifications, ii) to make the international science community, ESA and its member states, conscious that there is an opportunity to supply a series of entry probes as part of future international collaborations, for example as part of the future NASA flagship mission towards Uranus (Uranus Orbiter Probe) or to any future NASA-led mission to the outer planets for an affordable budget, and iii) to demonstrate that an M-class budget could even fund several entry probes with well-prioritized science objectives. The model payload capabilities of each concept will be defined according to a carefully-designed science traceability matrix. Two extreme concepts shall be investigated by the GEPP Consortium, namely a highly capable parachute-descent probe including a typical payload of 30 kg of scientific instruments down to 10 bars, and a smaller parachute-descent probe designed to address top priority science objectives with selected key measurements that would address the ESA Cosmic Vision 2050 science objectives. This presentation will detail the scientific objectives for each entry probe design, as well as the content, organization and planning of the study, which is assumed to be completed by the end of 2025.Publicación Acceso Abierto Dust Lifting Through Surface Albedo Changes at Jezero Crater, Mars(Advancing Earth and Space Science (AGU), 2023-03-22) Vicente Retortillo, Álvaro; Martínez, Germán M.; Lemmon, M. T.; Hueso, R.; Johnson, J. R.; Sullivan, Robert; Newman, C. E.; Sebastián, E.; Toledo, D.; Apéstigue, Víctor; Arruego, Ignacio; Munguira, A.; Sánchez Lavega, Agustín; Murdoch, N.; Gillier, M.; Stott, A.; Mora Sotomayor, L.; Bertrand, T.; Tamppari, L. K.; De la Torre Juárez, M.; Rodríguez Manfredi, J. A.; Agencia Estatal de Investigación (AEI); National Aeronautics and Space Administration (NASA); Comunidad de Madrid; Centro de Astrobiología del Instituto Nacional de Técnica Aeroespacial y CSIC, MDM-2017-0737We identify temporal variations in surface albedo at Jezero crater using first-of-their-kind high-cadence in-situ measurements of reflected shortwave radiation during the first 350 sols of the Mars 2020 mission. Simultaneous Mars Environmental Dynamics Analyzer (MEDA) measurements of pressure, radiative fluxes, winds, and sky brightness indicate that these albedo changes are caused by dust devils under typical conditions and by a dust storm at Ls ∼ 155°. The 17% decrease in albedo caused by the dust storm is one order of magnitude larger than the most apparent changes caused during quiescent periods by dust devils. Spectral reflectance measurements from Mastcam-Z images before and after the storm indicate that the decrease in albedo is mainly caused by dust removal. The occurrence of albedo changes is affected by the intensity and proximity of the convective vortex, and the availability and mobility of small particles at the surface. The probability of observing an albedo change increases with the magnitude of the pressure drop (ΔP): changes were detected in 3.5%, 43%, and 100% of the dust devils with ΔP < 2.5 Pa, ΔP > 2.5 Pa and ΔP > 4.5 Pa, respectively. Albedo changes were associated with peak wind speeds above 15 m·s−1. We discuss dust removal estimates, the observed surface temperature changes coincident with albedo changes, and implications for solar-powered missions. These results show synergies between multiple instruments (MEDA, Mastcam-Z, Navcam, and the Supercam microphone) that improve our understanding of aeolian processes on Mars.Publicación Acceso Abierto The sound of a Martian dust devil(Nature, 2022-12-13) Murdoch, N.; Stott, A. E.; Gillier, M.; Hueso, R.; Lemmon, M. T.; Martínez, Germán M.; Apéstigue, Víctor; Toledo, D.; Lorenz, R. D.; Chide, B.; Munguira, A.; Sánchez Lavega, Agustín; Vicente Retortillo, Álvaro; Newman, C. E.; Maurice, Sylvestre; De la Torre Juárez, M.; Bertrand, T.; Banfield, D.; Navarro López, Sara; Marín, M.; Torres, J.; Gómez Elvira, J.; Jacob, Xavier; Cadu, A.; Sournac, A.; Rodríguez Manfredi, J. A.; Mimoun, D.; National Aeronautics and Space Administration (NASA); Centre National D'Etudes Spatiales (CNES); NASA Jet Propulsion Laboratory (JPL); Comunidad de Madrid; Gobierno Vasco; Agencia Estatal de Investigación (AEI); Los Alamos National Laboratory; Centro de Astrobiología del Instituto Nacional de Técnica Aeroespacial y CSIC, MDM-2017-0737Dust devils (convective vortices loaded with dust) are common at the surface of Mars, particularly at Jezero crater, the landing site of the Perseverance rover. They are indicators of atmospheric turbulence and are an important lifting mechanism for the Martian dust cycle. Improving our understanding of dust lifting and atmospheric transport is key for accurate simulation of the dust cycle and for the prediction of dust storms, in addition to being important for future space exploration as grain impacts are implicated in the degradation of hardware on the surface of Mars. Here we describe the sound of a Martian dust devil as recorded by the SuperCam instrument on the Perseverance rover. The dust devil encounter was also simultaneously imaged by the Perseverance rover’s Navigation Camera and observed by several sensors in the Mars Environmental Dynamics Analyzer instrument. Combining these unique multi-sensorial data with modelling, we show that the dust devil was around 25 m large, at least 118 m tall, and passed directly over the rover travelling at approximately 5 m s−1. Acoustic signals of grain impacts recorded during the vortex encounter provide quantitative information about the number density of particles in the vortex. The sound of a Martian dust devil was inaccessible until SuperCam microphone recordings. This chance dust devil encounter demonstrates the potential of acoustic data for resolving the rapid wind structure of the Martian atmosphere and for directly quantifying wind-blown grain fluxes on Mars.Publicación Acceso Abierto MOURA magnetometer for Mars MetNet Precursor Mission. Its potential for an in situ magnetic environment and surface characterization(Universidad Complutense de Madrid, 2016-10-14) Díaz Michelena, Marina; Sanz, Ruy; Belén Fernández, A.; De Manuel, V.; Cerdán, M. F.; Apéstigue, Víctor; Domínguez, J. A.; González Fernández, Luis Miguel ; Guerrero, H.; Dolores Sabau, M.; Kilian, R.; Baeza, O.; Ríos, F.; Herraiz, M.; Vázquez, L.; Tordesillas, J. M.; Covisa, P.; Aguado, J.; Ministerio de Economía y Competitividad (MINECO)El magnetómetro y gradiómetro MOURA forma parte de la instrumentación científica de la misión precursora de MetNet a Marte. En este trabajo se describen los objetivos de esta investigación, se recopilan las tareas de diseño y desarrollo del mismo así como su posterior calibración y se muestran las principales acciones de demostración emprendidas con el instrumento que muestran su capacidad para medidas magnéticas a bordo de aterrizadores y rovers. MOURA magnetometer and gradiometer is part of the scientific instrumentation for Mars MetNet Precursor mission. This work describes the objective of the investigation, summarizes the work done in the design and development of the sensor as well as its calibration, and shows the demonstration campaigns to show the potential of such instrument for planetary landers and roversPublicación Restringido Thermal challenges in the deployment of an Environmental Network on the Mars Surface through miniature probes(ESA, 2024-10-09) Gonzalo Melchor, Alejandro; Arruego, Ignacio; Apéstigue, Víctor; Martínez Oter, Javier; Bastide, Laurent; Azcue, J.; Liaño, Gabriel; Caballero, Nieves; Torres, JosefinaOver the last decades, several missions have successfully landed on the Mars Surface, placing scientific instrumentation onboard landers and rovers in different individual landing sites. However, a qualitative leap in “in-situ” climate science on the red planet could happen via larger-scale observations. MarsConnect is an INTA project that aims to develop microprobes with scientific instruments that, thanks to their reduced mass and volume, could be deployed on the Martian surface in a large number to set up planetary atmospheric networks. The 10-12 kg probe consists of a rigid aero-shell that provides both stability and heat shielding during the descent, avoiding the complexity of supersonically deployed parachutes, propulsion systems or inflatable technologies. Aerothermal loads during the re-entry phase drive the sizing of the Thermal Protection System (TPS), that guarantees the probe’s structural integrity and proper internal temperatures. Preliminary conservative estimations for a range of trajectories and atmospheric conditions yield figures at the stagnation point of 210 W/cm² for peak thermal flux and of 10.000 J/cm² for integral thermal load. The aeroshell encloses a ~6 kg, 3-section, hard impact penetrator (terminal velocity < 140 m/s), that can accommodate up to 1 kg of payload. Once on the Mars surface, most of the equipment relies on its wide allowable temperature range, heritage of the miniaturized instrumentation already qualified for past missions to Mars. The penetrator also includes a highly insulated “warm compartment” for components required to be maintained within more stringent limits. The landing site latitude will determine the illumination profile along the Martian year, and hence the maximum available power that can be obtained by the lander solar cells and the necessary storage capacity of the batteries to survive the Martian night. The current talk will describe the different thermal environments throughout the mission that are critical for the dimensioning of the Mars Connect probes as well as provide a glimpse into the preliminary design concepts proposed in the frame of the project feasibility study.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 Acceso Abierto The diverse meteorology of Jezero crater over the first 250 sols of Perseverance on Mars(Nature Publishing Group, 2023-01-09) Rodríguez Manfredi, J. A.; De la Torre Juárez, M.; Sánchez Lavega, Agustín; Hueso, R.; Martínez, Germán M.; Lemmon, M. T.; Newman, C. E.; Munguira, A.; Hieta, M.; Tamppari, L. K.; Polkko, J.; Toledo, D.; Sebastian, D.; Smith, Michael D.; Jaakonaho, I.; Genzer, María; Vicente Retortillo, Álvaro; Viúdez Moreiras, Daniel; Ramos, Miguel; Saiz López, A.; Lepinette Malvitte, A.; Wolff, Michael; Sullivan, R. J.; Gómez Elvira, J.; Apéstigue, Víctor; Conrad, P.; Del Río Gaztelurrutia, T.; Murdoch, N.; Arruego, Ignacio; Banfield, D.; Boland, J.; Brown, Adrian Jon; Ceballos Cáceres, J.; Domínguez Pumar, M.; Espejo, S.; Fairén, A.; Ferrándiz Guibelalde, Ricardo; Fischer, E.; García Villadangos, M.; Giménez Torregrosa, S.; Gómez Gómez, F.; Guzewich, Scott; Harri, Ari-Matti; Jiménez Martín, Juan José; Jiménez, V.; Makinen, Terhi; Marín Jiménez, M.; Martín-Rubio, Carolina; Martín Soler, J.; Molina, A.; Mora Sotomayor, L.; Navarro López, Sara; Peinado, V.; Pérez Grande, I. ; Pla García, J.; Postigo, M.; Prieto-Ballesteros, Olga; Rafkin, Scot C. R.; Richardson, M. I.; Romeral, J.; Romero Guzmán, Catalina; Savijärvi, H.; Schofield, J. T.; Torres, J.; Urquí, R.; Zurita, S.; NASA Jet Propulsion Laboratory (JPL); National Aeronautics and Space Administration (NASA); Instituto Nacional de Técnica Aeroespacial (INTA); European Commission (EC); Ministerio de Economía y Competitividad (MINECO); Agencia Estatal de Investigación (AEI); California Institute of Technology (CIT); Centro de Astrobiología del Instituto Nacional de Técnica Aeroespacial y CSIC, MDM-2017-0737NASA’s Perseverance rover’s Mars Environmental Dynamics Analyzer is collecting data at Jezero crater, characterizing the physical processes in the lowest layer of the Martian atmosphere. Here we present measurements from the instrument’s first 250 sols of operation, revealing a spatially and temporally variable meteorology at Jezero. We find that temperature measurements at four heights capture the response of the atmospheric surface layer to multiple phenomena. We observe the transition from a stable night-time thermal inversion to a daytime, highly turbulent convective regime, with large vertical thermal gradients. Measurement of multiple daily optical depths suggests aerosol concentrations are higher in the morning than in the afternoon. Measured wind patterns are driven mainly by local topography, with a small contribution from regional winds. Daily and seasonal variability of relative humidity shows a complex hydrologic cycle. These observations suggest that changes in some local surface properties, such as surface albedo and thermal inertia, play an influential role. On a larger scale, surface pressure measurements show typical signatures of gravity waves and baroclinic eddies in a part of the seasonal cycle previously characterized as low wave activity. These observations, both com
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