SHARAD Sounding Radar on the Mars Reconnaissance Orbiter Roberto Seu,' Roger J
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Wind-Eroded Stratigraphy on the Floor of a Noachian Impact Crater, Noachis Terra, Mars
Third Conference on Early Mars (2012) 7066.pdf WIND-ERODED STRATIGRAPHY ON THE FLOOR OF A NOACHIAN IMPACT CRATER, NOACHIS TERRA, MARS. R. P. Irwin III1,2, J. J. Wray3, T. A. Maxwell1, S. C. Mest2,4, and S. T. Hansen3, 1Center for Earth and Planetary Studies, National Air and Space Museum, Smithsonian Institution, MRC 315, 6th St. at Independence Ave. SW, Washington DC 20013, [email protected], [email protected]. 2Planetary Science Institute, 1700 E. Fort Lowell, Suite 106, Tucson AZ 85719, [email protected]. 3School of Earth and Atmospheric Sciences, Georgia Institute of Technology, 311 Ferst Drive, Atlanta GA 30332-0340, [email protected], [email protected]. 4Planetary Geodynamics Laboratory, Code 698, NASA Goddard Space Flight Center, Greenbelt MD 20771. Introduction: Detailed stratigraphic and spectral cular 12-km depression (a possible highly degraded studies of outcrops exposed in craters and other basins crater) on the southern side. The former received in- have significantly advanced the understanding of early ternal drainage from the north and east, whereas part Mars. Most studies have focused on high-relief sec- of the southern wall drained to the latter (Fig. 2). tions exposed by aeolian deflation, such as those in Gale crater, Arabia Terra, and Valles Marineris [1–3]. Many flat-floored Noachian degraded craters also have wind-eroded strata, suggesting that they lack a cap rock of Gusev-type basalts [4,5]. This study focuses on the youngest materials exposed on the wind-eroded floor of an unnamed Noachian degraded crater in Noachis Terra, Mars. The crater is centered at 20.2ºS, 42.6ºE and is 52 km in diameter. -
JUICE Red Book
ESA/SRE(2014)1 September 2014 JUICE JUpiter ICy moons Explorer Exploring the emergence of habitable worlds around gas giants Definition Study Report European Space Agency 1 This page left intentionally blank 2 Mission Description Jupiter Icy Moons Explorer Key science goals The emergence of habitable worlds around gas giants Characterise Ganymede, Europa and Callisto as planetary objects and potential habitats Explore the Jupiter system as an archetype for gas giants Payload Ten instruments Laser Altimeter Radio Science Experiment Ice Penetrating Radar Visible-Infrared Hyperspectral Imaging Spectrometer Ultraviolet Imaging Spectrograph Imaging System Magnetometer Particle Package Submillimetre Wave Instrument Radio and Plasma Wave Instrument Overall mission profile 06/2022 - Launch by Ariane-5 ECA + EVEE Cruise 01/2030 - Jupiter orbit insertion Jupiter tour Transfer to Callisto (11 months) Europa phase: 2 Europa and 3 Callisto flybys (1 month) Jupiter High Latitude Phase: 9 Callisto flybys (9 months) Transfer to Ganymede (11 months) 09/2032 – Ganymede orbit insertion Ganymede tour Elliptical and high altitude circular phases (5 months) Low altitude (500 km) circular orbit (4 months) 06/2033 – End of nominal mission Spacecraft 3-axis stabilised Power: solar panels: ~900 W HGA: ~3 m, body fixed X and Ka bands Downlink ≥ 1.4 Gbit/day High Δv capability (2700 m/s) Radiation tolerance: 50 krad at equipment level Dry mass: ~1800 kg Ground TM stations ESTRAC network Key mission drivers Radiation tolerance and technology Power budget and solar arrays challenges Mass budget Responsibilities ESA: manufacturing, launch, operations of the spacecraft and data archiving PI Teams: science payload provision, operations, and data analysis 3 Foreword The JUICE (JUpiter ICy moon Explorer) mission, selected by ESA in May 2012 to be the first large mission within the Cosmic Vision Program 2015–2025, will provide the most comprehensive exploration to date of the Jovian system in all its complexity, with particular emphasis on Ganymede as a planetary body and potential habitat. -
MARS an Overview of the 1985–2006 Mars Orbiter Camera Science
MARS MARS INFORMATICS The International Journal of Mars Science and Exploration Open Access Journals Science An overview of the 1985–2006 Mars Orbiter Camera science investigation Michael C. Malin1, Kenneth S. Edgett1, Bruce A. Cantor1, Michael A. Caplinger1, G. Edward Danielson2, Elsa H. Jensen1, Michael A. Ravine1, Jennifer L. Sandoval1, and Kimberley D. Supulver1 1Malin Space Science Systems, P.O. Box 910148, San Diego, CA, 92191-0148, USA; 2Deceased, 10 December 2005 Citation: Mars 5, 1-60, 2010; doi:10.1555/mars.2010.0001 History: Submitted: August 5, 2009; Reviewed: October 18, 2009; Accepted: November 15, 2009; Published: January 6, 2010 Editor: Jeffrey B. Plescia, Applied Physics Laboratory, Johns Hopkins University Reviewers: Jeffrey B. Plescia, Applied Physics Laboratory, Johns Hopkins University; R. Aileen Yingst, University of Wisconsin Green Bay Open Access: Copyright 2010 Malin Space Science Systems. This is an open-access paper distributed under the terms of a Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. Abstract Background: NASA selected the Mars Orbiter Camera (MOC) investigation in 1986 for the Mars Observer mission. The MOC consisted of three elements which shared a common package: a narrow angle camera designed to obtain images with a spatial resolution as high as 1.4 m per pixel from orbit, and two wide angle cameras (one with a red filter, the other blue) for daily global imaging to observe meteorological events, geodesy, and provide context for the narrow angle images. Following the loss of Mars Observer in August 1993, a second MOC was built from flight spare hardware and launched aboard Mars Global Surveyor (MGS) in November 1996. -
Mars Subsurface Water Ice Mapping (Swim): Radar Subsurface Reflectors
50th Lunar and Planetary Science Conference 2019 (LPI Contrib. No. 2132) 2069.pdf MARS SUBSURFACE WATER ICE MAPPING (SWIM): RADAR SUBSURFACE REFLECTORS. A. M. Bramson1, E. I. Petersen1, Z. M. Bain2, N. E. Putzig2, G. A. Morgan2, M. Mastrogiuseppe3, M. R. Perry2, I. B. Smith2, H. G. Sizemore2, D. M. H. Baker4, R. H. Hoover5, B. A. Campbell6. 1Lunar and Planetary Laboratory, University of Arizona ([email protected]), 2Planetary Science Institute, 3California Institute of Technology, 4NASA Goddard Space Flight Center, 5Southwest Research Institute, 6Smithsonian Institution Introduction: The Subsurface Water Ice Mapping Consistency Mapping: To enable a quantitative as- (SWIM) in the Northern Hemisphere of Mars, supports sessment of how consistent (or inconsistent) the various an effort by NASA’s Mars Exploration Program to de- remote sensing datasets are with the presence of shallow termine in situ resource availability. We are performing (<5 m) and deep (>5 m) ice across these regions, we in- global reconnaissance mapping as well as focused troduce the SWIM Equation. Outlined in detail by Perry multi-dataset mapping from 0º to 60ºN in four longitude et al. [this LPSC], the SWIM Equation yields con- bands: “Arcadia” (150–225ºE, which also contains our sistency values ranging between +1 and -1, where +1 pilot study region), “Acidalia” (290–360ºE), “Onilus” means that the data are consistent with the presence of (0–70ºE, which covers Deuteronilus and Protonilus ice, 0 means that the data give no indications of the pres- Mensae), and “Utopia” (70–150ºE). Our maps are being ence or absence of ice, and -1 means that the data are made available to the community on the SWIM Project inconsistent with the presence of ice. -
+ New Horizons
Media Contacts NASA Headquarters Policy/Program Management Dwayne Brown New Horizons Nuclear Safety (202) 358-1726 [email protected] The Johns Hopkins University Mission Management Applied Physics Laboratory Spacecraft Operations Michael Buckley (240) 228-7536 or (443) 778-7536 [email protected] Southwest Research Institute Principal Investigator Institution Maria Martinez (210) 522-3305 [email protected] NASA Kennedy Space Center Launch Operations George Diller (321) 867-2468 [email protected] Lockheed Martin Space Systems Launch Vehicle Julie Andrews (321) 853-1567 [email protected] International Launch Services Launch Vehicle Fran Slimmer (571) 633-7462 [email protected] NEW HORIZONS Table of Contents Media Services Information ................................................................................................ 2 Quick Facts .............................................................................................................................. 3 Pluto at a Glance ...................................................................................................................... 5 Why Pluto and the Kuiper Belt? The Science of New Horizons ............................... 7 NASA’s New Frontiers Program ........................................................................................14 The Spacecraft ........................................................................................................................15 Science Payload ...............................................................................................................16 -
SWIFTS and SWIFTS-LA: Two Concepts for High Spectral Resolution Static Micro-Imaging Spectrometers
EPSC Abstracts Vol. 9, EPSC2014-439-1, 2014 European Planetary Science Congress 2014 EEuropeaPn PlanetarSy Science CCongress c Author(s) 2014 SWIFTS and SWIFTS-LA: two concepts for high spectral resolution static micro-imaging spectrometers E. Le Coarer(1), B. Schmitt(1), N. Guerineau (2), G. Martin (1) S. Rommeluere (2), Y. Ferrec (2) F. Simon (1) F. Thomas (1) (1) Univ. UGA ,CNRS, Lab. IPAG, Grenoble, France. (2) ONERA/DOTA Palaiseau France ([email protected] grenoble.fr). Abstract All these instruments use either optical gratings, Fourier transform or AOTF spectrometers. The two SWIFTS (Stationary-Wave Integrated Fourier first types need moving mirrors to scan spectrally Transform Spectrometer) represents a family of very thus adding complexity and failure risk in space. The compact spectrometers based on detection of interesting solution of AOTF, without moving part standing waves for which detectors play itself a role (only piezo) is however limited in resolution to a few in the interferential detection mechanism. The aim of cm-1 due to limitation in monocrystal size (fragile). this paper is to illustrate how these spectrometers can Strong limitations of these instruments in terms of be used to build efficient imaging spectrometers for performances (spectral & spatial resolution and range, planetary exploration inside dm3 instrumental volume. S/N ratio) come from their already large mass, The first mode (SWIFTS) is devoted to high spectral volume, and power consumption. Further increasing resolving power imaging (R~10000-50000) for one of these characteristics will be at the cost of even 40x40 pixels field of view. The second mode bigger instruments. -
An Orthoimage Map Using Data Obtained from the Mars Orbiter Camera of Mars Global Surveyor
An Orthoimage map using data obtained from the Mars Orbiter Camera of Mars Global Surveyor G. Niedermaier1,2, M. WŠhlisch1, F. Scholten1, F. Wewel1, Th. Roatsch1, R. Jaumann1, Th. Wintges2 (1 German Aerospace Center (DLR), Institute of Space Sensor Technology and Planetary Exploration, Berlin-Adlershof, 2University for Applied Sciences Munich (FHM), e-mail: [email protected]) Introduction. A basic requirement for the planning of future, perhaps even manned Mars missions are precise and high resolution maps of our neighbour planet and, especially, of the landing area. Here we present a new orthoimage map of Mars using data obtained from the Mars Orbiter Camera (MOC) of the Mars Global Surveyor (MGS). Since 1998, the National Aeronautics and Space Agency (NASA) uses the MGS for exploration and mapping of the global Martian surface. The new map covers the Mars surface from 0° to 180° West and from 60° South to 60° North, respectively, with a resolution of 231m/pixel. For map composing digital image processing methods have been used. Furthermore, we have succeeded to de- velop a processing method for composing image mosaics based on MOC data. This method may be used for composing image mosaics using CCD line camera data and is applicable also for other mars missions, whenever a CCD line camera is employed. Methods. Image data processing has been performed using multiple Video Image Commu- nication and Retrieval (VICAR) programs, developed by the Jet Propulsion Laboratory (JPL), DLR and the Technical University of Berlin (TUB), Department of Photogrammetry and Cartography. Also United States Geological Survey (USGS) Integrated Software for Imagers and Spectrometers (ISIS) programs were used. -
Exploration of Mars by the European Space Agency 1
Exploration of Mars by the European Space Agency Alejandro Cardesín ESA Science Operations Mars Express, ExoMars 2016 IAC Winter School, November 20161 Credit: MEX/HRSC History of Missions to Mars Mars Exploration nowadays… 2000‐2010 2011 2013/14 2016 2018 2020 future … Mars Express MAVEN (ESA) TGO Future ESA (ESA- Studies… RUSSIA) Odyssey MRO Mars Phobos- Sample Grunt Return? (RUSSIA) MOM Schiaparelli ExoMars 2020 Phoenix (ESA-RUSSIA) Opportunity MSL Curiosity Mars Insight 2020 Spirit The data/information contained herein has been reviewed and approved for release by JPL Export Administration on the basis that this document contains no export‐controlled information. Mars Express 2003-2016 … First European Mission to orbit another Planet! First mission of the “Rosetta family” Up and running since 2003 Credit: MEX/HRSC First European Mission to orbit another Planet First European attempt to land on another Planet Original mission concept Credit: MEX/HRSC December 2003: Mars Express Lander Release and Orbit Insertion Collission trajectory Bye bye Beagle 2! Last picture Lander after release, release taken by VMC camera Insertion 19/12/2003 8:33 trajectory Credit: MEX/HRSC Beagle 2 was found in January 2015 ! Only 6km away from landing site OK Open petals indicate soft landing OK Antenna remained covered Lessons learned: comms at all time! Credit: MEX/HRSC Mars Express: so many missions at once Mars Mission Phobos Mission Relay Mission Credit: MEX/HRSC Mars Express science investigations Martian Moons: Phobos & Deimos: Ionosphere, surface, -
Estimated Attenuation Rates Using GPR and TDR in Volcanic Depos
PUBLICATIONS Journal of Geophysical Research: Planets RESEARCH ARTICLE Electromagnetic signal penetration in a planetary soil 10.1002/2016JE005192 simulant: Estimated attenuation rates using GPR Key Points: and TDR in volcanic deposits on Mount Etna • GPR methodologies for evaluating the loss tangent of volcanic sediments S. E. Lauro1 , E. Mattei1 , B. Cosciotti1 , F. Di Paolo1 , S. A. Arcone2, M. Viccaro3,4 , • Characterization of electrical 1 properties of a planetary soil simulant and E. Pettinelli • Comparison between GPR and TDR 1 2 measurements Dipartimento di Matematica e Fisica, Università degli Studi Roma TRE, Rome, Italy, US Army ERDC-CRREL, Hanover, New Hampshire, USA, 3Dipartimento di Scienze Biologiche Geologiche e Ambientali, Università degli Studi di Catania, Catania, Italy, 4Osservatorio Etneo, Istituto Nazionale di Geofisica e Vulcanologia, Catania, Italy Correspondence to: S. E. Lauro, Abstract Ground-penetrating radar (GPR) is a well-established geophysical terrestrial exploration method [email protected] and has recently become one of the most promising for planetary subsurface exploration. Several future landing vehicles like EXOMARS, 2020 NASA ROVER, and Chang’e-4, to mention a few, will host GPR. A GPR Citation: survey has been conducted on volcanic deposits on Mount Etna (Italy), considered a good analogue for Lauro, S. E., E. Mattei, B. Cosciotti, F. Di Paolo, S. A. Arcone, M. Viccaro, and Martian and Lunar volcanic terrains, to test a novel methodology for subsoil dielectric properties estimation. E. Pettinelli (2017), Electromagnetic The stratigraphy of the volcanic deposits was investigated using 500 MHz and 1 GHz antennas in two different signal penetration in a planetary soil configurations: transverse electric and transverse magnetic. -
A Compressive-Sensing-Based Approach to Reconstruct Regolith Structure from Lunar Penetrating Radar Data at the Chang’E-3 Landing Site
remote sensing Article A Compressive-Sensing-Based Approach to Reconstruct Regolith Structure from Lunar Penetrating Radar Data at the Chang’E-3 Landing Site Kun Wang 1,2 , Zhaofa Zeng 1,2,*, Ling Zhang 1,2, Shugao Xia 3 and Jing Li 1,2 1 College of Geo-Exploration Science and Technology, Jilin University, Changchun 130026, China; [email protected] (K.W.); [email protected] (L.Z.); [email protected] (J.L.) 2 Key Laboratory of Applied Geophysics, Ministry of Natural Resources of PRC, Changchun 130026, China 3 Delaware State University, Dover, DE 19901, USA ; [email protected] * Correspondence: [email protected] Received: 18 October 2018; Accepted: 27 November 2018; Published: 30 November 2018 Abstract: Lunar Penetrating Radar (LPR) is one of the important scientific systems onboard the Yutu lunar rover for the purpose of detecting the lunar regolith and the subsurface geologic structures of the lunar regolith, providing the opportunity to map the subsurface structure and vertical distribution of the lunar regolith with a high resolution. In this paper, in order to improve the capability of identifying response signals caused by discrete reflectors (such as meteorites, basalt debris, etc.) beneath the lunar surface, we propose a compressive sensing (CS)-based approach to estimate the amplitudes and time delays of the radar signals from LPR data. In this approach, the total-variation (TV) norm was used to estimate the signal parameters by a set of Fourier series coefficients. For this, we chose a nonconsecutive and random set of Fourier series coefficients to increase the resolution of the underlying target signal. -
SHARAD Observations of Recent Geologic Features on Mars
EPSC Abstracts Vol. 6, EPSC-DPS2011-1591-1, 2011 EPSC-DPS Joint Meeting 2011 c Author(s) 2011 SHARAD observations of recent geologic features on Mars N. E. Putzig (1), R. J. Phillips (1), J. W. Holt (2), I. B. Smith (2), L. M. Carter (3), and R. Seu (4) for the SHARAD Team. (1) Southwest Research Institute, Colorado, USA ([email protected]), (2) University of Texas at Austin, Texas, USA, NASA Goddard Space Flight Center, Maryland, USA, (4) Sapienza University of Rome, Italy. Abstract NPLD stratigraphy consists of packets of brightly reflective layers alternating with relatively non- The Shallow Radar (SHARAD) instrument on the reflective zones, and these sequences can be Mars Reconnaissance Orbiter (MRO) observes a correlated to orbit cycles, suggesting an age of ~4.2 variety of recent features on Mars, including deposits Ma [2]. In detail, the radar shows unconformities, of water ice at both poles and in the mid-latitudes, either within the reflective sequences or at their boundaries (Fig. 1). A history of alternating periods solid CO2 in the south polar region, and volcanics in the tropics and mid-latitudes. SHARAD’s view of of non-uniform deposition and erosion is recorded by subsurface layers sheds light on the history of these structures. In the upper ~500 m, discontinuities deposition and erosion in these terrains, with that trace to troughs observable at the surface map implications for the cycle of volatile exchange and out paths of trough migration over time. The for recent volcanism. poleward migration and SHARAD-observed thickness variations adjacent to the migration path are consistent with a mechanism of katabatic winds 1. -
The Cassini Ultraviolet Imaging Spectrograph Investigation
THE CASSINI ULTRAVIOLET IMAGING SPECTROGRAPH INVESTIGATION 1, 1 1 LARRY W. ESPOSITO ∗, CHARLES A. BARTH , JOSHUA E. COLWELL , GEORGE M. LAWRENCE1, WILLIAM E. McCLINTOCK1,A. IAN F. STEWART1, H. UWE KELLER2, AXEL KORTH2, HANS LAUCHE2, MICHEL C. FESTOU3,ARTHUR L. LANE4, CANDICE J. HANSEN4, JUSTIN N. MAKI4,ROBERT A. WEST4, HERBERT JAHN5, RALF REULKE5, KERSTIN WARLICH5, DONALD E. SHEMANSKY6 and YUK L. YUNG7 1University of Colorado, Laboratory for Atmospheric and Space Physics, 1234 Innovation Drive, Boulder, CO 80303, U.S.A. 2Max-Planck-Institut fur¨ Aeronomie, Max-Planck-Strasse 2, 37191 Katlenburg-Lindau, Germany 3Observatoire Midi-Pyren´ ees,´ 14 avenue E. Belin, F31400 Toulouse, France 4JetPropulsion Laboratory, 4800 Oak Grove Drive, Pasadena, CA 91109, U.S.A. 5Deutsches Zentrum fur¨ Luft und Raumfahrt, Institut fur¨ Weltraumsensorik und Planetenerkundung, Rutherford Strasse 2, 12489 Berlin, Germany 6University of Southern California, Department of Aerospace Engineering, 854 W. 36th Place, Los Angeles, CA 90089, U.S.A. 7California Institute of Technology, Division of Geological and Planetary Sciences, MS 150-21, Pasadena, CA 91125, U.S.A. (∗Author for correspondence: E-mail: [email protected]) (Received 8 July 1999; Accepted in final form 18 October 2000) Abstract. The Cassini Ultraviolet Imaging Spectrograph (UVIS) is part of the remote sensing payload of the Cassini orbiter spacecraft. UVIS has two spectrographic channels that provide images and spectra covering the ranges from 56 to 118 nm and 110 to 190 nm. A third optical path with a solar blind CsI photocathode is used for high signal-to-noise-ratio stellar occultations by rings and atmospheres. A separate Hydrogen Deuterium Absorption Cell measures the relative abundance of deuterium and hydrogen from their Lyman-α emission.