DOCSLIB.ORG

DART – Double Asteroid Redirection Test Status NASA’S Mission to Demonstrate Asteroid Deflection with a Kinetic Impactor

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
DART – Double Asteroid Redirection Test Status NASA’S Mission to Demonstrate Asteroid Deflection with a Kinetic Impactor DART – Double Asteroid Redirection Test Status NASA’s mission to demonstrate asteroid deflection with a kinetic impactor Goddard Space Flight Center Elena Adams Johnson Space Center Langley Research Center Mission Systems Engineer Glenn Research Center Marshall Space Flight Center January 30, 2019 Planetary Defense Coordination Office DART – Double Asteroid Redirection Test 1 NASA Planetary Defense Coordination Office (PDCO): established 2016 DART – Double Asteroid Redirection Test 2 Launch June 2021 March 2022 IMPACT: October 2022 Recent and Upcoming 2001 CB21 flyby Mission Milestones: S-type, 578 meters, • KDP-C (Confirmation): 3.3-hour rotation rate 17 Aug, 2018 • Critical Design Review LICIA Cube (CDR) 27 June, 2019 (Light Italian Cubesat • KDP-D (System for Imaging of Asteroids) Integration):16 Mar ASI contribution 2020 DART Spacecraft 65803 Didymos 540 kg arrival mass Didymos-B (1996 GT) Didymos-A 12.5 m × 2.4 m × 2.0 m 163 meters 1,180-meter separation 780 meters, S-type 6 km/s closing speed 11.92-hour orbital period between centers of A and B 2.26-hour rotation period Earth-Based Observations • Target the binary asteroid Didymos system 0.07 AU range at impact Predicted ~8-minute change • Impact Didymos-B and change its orbital period in binary orbit period • Measure the period change from Earth DART – Double Asteroid Redirection Test 3 DART: Key Technologies DART will demonstrate key technologies for future NASA missions. Roll Out Solar Arrays (ROSA) Powered flight, demonstrated on ISS previously Coresat Avionics Integrated system-on-a-chip FPGA processing Transformational Solar Arrays Concentrators, providing 5x times power Autonomous SmartNav system NEXT-C Ion Propulsion Engine of current state-of-the-art solar arrays, great at Jovian distances SmartNav autonomously directs DART will be the first flight of NASA’s DART to impact Didymos-B, Evolutionary Xenon Thruster- leveraging missile guidance Commercial (NEXT-C) ion propulsion Radial Line Slot Array algorithms developed at APL. engine. Planar low cost high efficiency high gain Uses Narrow Angle Camera antenna (DRACO) for detection. DART – Double Asteroid Redirection Test 4 DART Status Getting ready to Rock. • Mission is moving towards its Critical Design Review in June! • Baseline changes - Class C mission - DART is no longer a rideshare and will have its own launch vehicle Flight Heatpipes Ready - Added a CubeSat (see following slide) and transformational solar array demonstration • LSP is in process of acquiring a launch vehicle for DART - Selection to be finalized in early February, but with PPU Interface Box Testing government shutdown that has been delayed • Additional Didymos observations planned • NEXT-C project started flight production of the NEXT-C thruster and electronics NEXT-C simulators Harness Mockup DART – Double Asteroid Redirection Test 30 January 2019 5 Light Italian CubeSat for Imaging Asteroids LICIACube LICIACube Description • A very capable 6U CubeSat provided by Agenzia Spaziale Italiana Goals (ASI) 1- Impact Obtain multiple (at least three) - CubeSat contractor: Argotec ejecta plume images of DART impact ejecta • Based on Argomoon CubeSat that will be flying on EM-1 mission evolution plume over a span of times and phase angles, to allow estimation (first flight of SLS in 2020) of plume density structure • In process of solidifying payload, but Narrow Angle Camera at the 2- Impact Obtain multiple (> 3) images of least (goal of 1 m/ pixel resolution imagery) crater DART impact site having sufficient resolution to allow measurements of impact crater size and Current conops includes flyby of morphology Didymos ~ 5 min after DART 3 - Non- Obtain multiple (at least three) impact and downlinking data after impact images of the non-impact event hemisphere hemisphere of Didymos B 4 - Color/ Obtain images of the ejecta plume Preliminary Design Review (PDR) spectral and of asteroid target to in March 2019 imaging characterize color and spectral plume & variations Didymos DART – Double Asteroid Redirection Test 30 January 2019 6 Path To Terminal Guidance 2022 Intercept (~10.9M km; 6.8M miles from Earth)* Autonomous Navigation and Targeting 1. Launch 2. Cruise / Calibration 3. Target Detection 4. Deploy 6U CubeSat / Coarse Acquisition 6U CubeSat releases and executes a separation maneuver to trail DART <~2 days until impact> Flyby of PHA allows sensor calibration and control-gain tuning Weeks prior to impact, High Energy Escape <7 months until impact> DART s/c detects primary <Jun 15 – Oct 15 2021> <108 km from target> <30 days until impact> <108 km from target> <107 km from target> 5. Scene Classification 6. Target Selection 7. Homing Until Intercept 8. Impact Assessment Itokawa at 0.5 m/pix DRACO achieves the 50 cm/pixel target resolution requirement at 17 s before impact DART S/C counts and classifies With sufficient confidence, DART closely spaced objects S/C selects target and locks on <3 hours until impact> <1.5 hours until impact> SMART Nav executes precision maneuvers Earth tracking & 6U CubeSat <32,000 km from target> <65,000 km from target> and is robust to target uncertainties images quantify intercept success <Executed until final 2 minutes> <Up to 3 months> <6.0 km/s Impact> * 16 months total flight time.
Load more

Recommended publications
  • DART Mission Update
    Kinetic Impactor Andy Cheng JHU/APL 15 Nov 2018 DART Mission Update Goddard Space Flight Center Johnson Space Center Langley Research Center Glenn Research Center Marshall Space Flight Center Planetary Defense Coordination Office 1 Regimes of Primary Applicability for Planetary Defense Mitigation Defending Planet Earth (2010) Zero PHAs National Academy of Sciences Deep Impact Recommendation: “the first priority for a space About 150 PHAs mission in the mitigation area is an experimental test of a kinetic impactor” About 5,000 PHAs DART is the first kinetic DART impact test at a realistic scale for planetary Too small to be Defending Planet Earth (2010) considered PHAs defense 2 Launch June 15, 2021 March 6, 2022 IMPACT: October 5, 2022 2001 CB21 flyby S-type, 578 meters, 3.3-hour rotation rate LICIA (Light Italian Cubesat for Imaging of Asteroids) ASI contribution, under consideration DART Spacecraft 65803 Didymos 560 kg arrival mass Didymos-B (1996 GT) Didymos-A 12.5 m × 2.4 m × 2.0 m 163 meters 1,180-meter separation 780 meters, S-type 6 km/s closing speed 11.92-hour orbital period between centers of A and B 2.26-hour rotation period Earth-Based Observations • Target the binary asteroid Didymos system 0.07 AU range at impact Predicted ~8-minute change • Impact Didymos-B and change its orbital period in binary orbit period • Measure the period change from Earth DART – Double Asteroid Redirection Test 3 DART Program Update .DART mission confirmed by NASA in August, 2018. DART is in PHASE C-D .NASA has re-affirmed decision to use NEXT- C ion propulsion system for DART Autonomous navigation .NASA will procure launch services for DART using imager to guide to target through NLS; LV selection is in process ─ DART will have dedicated LV .LICIACube, an ASI-contributed cubesat ─ Letters exchanged between NASA and ASI ─ Studying operations concept and cubesat NEXT-C ion propulsion accommodations on DART first flight 4 DART Ion Propulsion Mission First flight of NASA NEXT-C ion engine .
    [Show full text]
  • Robotic Asteroid Prospector
    Robotic Asteroid Prospector Marc M. Cohen1 Marc M. Cohen Architect P.C. – Astrotecture™, Palo Alto, CA, USA 94306-3864 Warren W. James2 V Infinity Research LLC. – Altadena, CA, USA Kris Zacny,3 Philip Chu, Jack Craft Honeybee Robotics Spacecraft Mechanisms Corporation – Pasadena, CA, USA This paper presents the results from the nine-month, Phase 1 investigation for the Robotic Asteroid Prospector (RAP). This project investigated several aspects of developing an asteroid mining mission. It conceived a Space Infrastructure Framework that would create a demand for in space-produced resources. The resources identified as potentially feasible in the near-term were water and platinum group metals. The project’s mission design stages spacecraft from an Earth Moon Lagrange (EML) point and returns them to an EML. The spacecraft’s distinguishing design feature is its solar thermal propulsion system (STP) that provides two functions: propulsive thrust and process heat for mining and mineral processing. The preferred propellant is water since this would allow the spacecraft to refuel at an asteroid for its return voyage to Cis- Lunar space thus reducing the mass that must be launched from the EML point. The spacecraft will rendezvous with an asteroid at its pole, match rotation rate, and attach to begin mining operations. The team conducted an experiment in extracting and distilling water from frozen regolith simulant. Nomenclature C-Type = Carbonaceous Asteroid EML = Earth-Moon Lagrange Point ESL = Earth-Sun Lagrange Point IPV = Interplanetary Vehicle M-Type = Metallic Asteroid NEA = Near Earth Asteroid NEO = Near Earth Object PGM = Platinum Group Metal STP = Solar Thermal Propulsion S-Type = Stony Asteroid I.
    [Show full text]
  • BOULDERS on ASTEROIDS DIDYMOS and DIMORPHOS: FUTURE DART-Liciacube OBSERVATIONS
    52nd Lunar and Planetary Science Conference 2021 (LPI Contrib. No. 2548) 1116.pdf BOULDERS ON ASTEROIDS DIDYMOS AND DIMORPHOS: FUTURE DART-LICIACube OBSERVATIONS M. Pajola1, A. Lucchetti1, S. Ivanovski2, G. Poggiali3,4, S. Ieva5, D. Perna5, E. Dotto5, V. Della Corte6, G. Cremonese1, M. Amoroso7, S. Pirrotta7, E. Mazzotta Epifani5, A. Cheng8, N. Chabot8, A. Rivkin8, O. Barnouin8, C. Ernst8, R.T. Daly8, M. Hirabayashi9, E. Asphaug10, S.R. Schwartz10, J.M. Trigo-Rodriguez11, E.G. Fahnestock12, P. Michel13, I. Bertini14, J.R. Brucato3, A. Capannolo15, B. Cotugno16, V. Di Tana16, I. Gai17, G. Impresario7, M. Lavagna15, A. Meneghin3, F. Miglioretti16, D. Modenini17, P. Palumbo14,6, A. Rossi18, E. Simioni1, S. Simonetti16, P. Tortora17, M. Zannoni17, G. Zanotti15, A. Zinzi19,7. 1INAF-Astronomical Observatory of Padova, Vic. Osservatorio 5, 35122 Padova, Italy ([email protected]); 2INAF Osservatorio Astronomico di Trieste, Trieste, Italy; 3INAF Osservatorio Astrofisico di Arcetri, Firenze, Italy; 4Università di Firenze, Dipartimento di Fisica e Astronomia, Sesto Fiorentino (Firenze), Italy; 5INAF Osservatorio Astronomico di Roma, Monte Porzio Catone (Roma), Italy; 6INAF Istituto di Astrofisica e Planetologia Spaziali, Roma, Italy; 7Agenzia Spaziale Italiana, via del Politecnico, 00133 Roma, Italy; 8Johns Hopkins University Applied Physics Laboratory, Laurel, MD-USA; 9Auburn University, Auburn, AL-USA; 10Lunar and Planetary Laboratory, University of Arizona, Tucson, AZ-USA; 11Institute of Space Sciences (IEEC-CSIC), Dept. of Astrophysics,
    [Show full text]
  • Appendix 1 1311 Discoverers in Alphabetical Order
    Appendix 1 1311 Discoverers in Alphabetical Order Abe, H. 28 (8) 1993-1999 Bernstein, G. 1 1998 Abe, M. 1 (1) 1994 Bettelheim, E. 1 (1) 2000 Abraham, M. 3 (3) 1999 Bickel, W. 443 1995-2010 Aikman, G. C. L. 4 1994-1998 Biggs, J. 1 2001 Akiyama, M. 16 (10) 1989-1999 Bigourdan, G. 1 1894 Albitskij, V. A. 10 1923-1925 Billings, G. W. 6 1999 Aldering, G. 4 1982 Binzel, R. P. 3 1987-1990 Alikoski, H. 13 1938-1953 Birkle, K. 8 (8) 1989-1993 Allen, E. J. 1 2004 Birtwhistle, P. 56 2003-2009 Allen, L. 2 2004 Blasco, M. 5 (1) 1996-2000 Alu, J. 24 (13) 1987-1993 Block, A. 1 2000 Amburgey, L. L. 2 1997-2000 Boattini, A. 237 (224) 1977-2006 Andrews, A. D. 1 1965 Boehnhardt, H. 1 (1) 1993 Antal, M. 17 1971-1988 Boeker, A. 1 (1) 2002 Antolini, P. 4 (3) 1994-1996 Boeuf, M. 12 1998-2000 Antonini, P. 35 1997-1999 Boffin, H. M. J. 10 (2) 1999-2001 Aoki, M. 2 1996-1997 Bohrmann, A. 9 1936-1938 Apitzsch, R. 43 2004-2009 Boles, T. 1 2002 Arai, M. 45 (45) 1988-1991 Bonomi, R. 1 (1) 1995 Araki, H. 2 (2) 1994 Borgman, D. 1 (1) 2004 Arend, S. 51 1929-1961 B¨orngen, F. 535 (231) 1961-1995 Armstrong, C. 1 (1) 1997 Borrelly, A. 19 1866-1894 Armstrong, M. 2 (1) 1997-1998 Bourban, G. 1 (1) 2005 Asami, A. 7 1997-1999 Bourgeois, P. 1 1929 Asher, D.
    [Show full text]
  • Exploration of the Binary Asteroid 65803 Didymos by the Hera Mission
    EPSC Abstracts Vol. 13, EPSC-DPS2019-583-1, 2019 EPSC-DPS Joint Meeting 2019 c Author(s) 2019. CC Attribution 4.0 license. Exploration of the binary asteroid 65803 Didymos by the Hera mission Michael Küppers (1), Patrick Michel (2), Ian Carnelli (3), Paolo Martino (4) and the Hera Team (1) ESA-ESAC, Villanueva de la Cañada, Spain ([email protected] (2) Université Côte d’Azur, Observatoire de la Côte d’Azur, CNRS, Laboratoire Lagrange, France (3) ESA HQ, Paris, France, (4) ESA-ESTEC, Noordwijk, The Netherlands Abstract Hera is ESA’s contribution to the international Asteroid Impact Deflection Assessment (AIDA) cooperation, targeting the demonstration of deflection of a hazardous near-earth asteroid [1,2]. Hera will also be the first in-depth investigation of a binary asteroid and make measurements that are relevant for the preparation of asteroid resource utilisation. Hera is foreseen to rendezvous with the binary near-Earth asteroid (65803) Didymos in 2026, four years after the impact of NASA’s Double Asteroid Redirection Test (DART) spacecraft. 1. Introduction Figure 1: Overview of the Hera mission scenario Hera is a small mission of opportunity whose primary objective is to observe the outcome of a kinetic impactor test and thus, to provide extremely 2. Exploration of Asteroid Didymos valuable information for possible future mitigation of by the Hera mission the impact of a hazardous asteroid [1]. It is part of the Asteroid Impact & Deflection Assessment (AIDA) mission, in which the second component is the Hera will monitor Didymos for several months, NASA Double Asteroid Redirection Test (DART) accurately measuring its dynamical state and mission, which aims to send an artificial projectile to completely mapping the surface with the Asteroid perform an asteroid deflection test [2].
    [Show full text]
  • Binary Asteroid Lightcurves
    BINARY ASTEROID LIGHTCURVES Asteroid Type Per1 Amp1 Per2 Amp2 Perorb Ds/Dp a/Dp Reference 22 Kalliope B 4.1483 0.53 B a Descamps, 08 B a 86.2896 Marchis, 08 B a 4.148 86.16 Marchis, 11w 41∗ Daphne B 5.988 0.45 B s 26.4 Conrad, 08 B s 38. Conrad, 08 B s 5.987981 27.289 2.46 Carry, 18 45 Eugenia M 5.699 0.30 B a 113. Merline, 99 B a Marchis, 06 M a Marchis, 07 M a Marchis, 08 B a 5.6991 114.38 Marchis, 11w 87 Sylvia M 5.184 0.50 M a 5.184 87.5904 Marchis, 05 M a 5.1836 87.59 Marchis, 11w 90∗ Antiope B 16.509 0.88 B f 16. Merline, 00 B f 16.509 0.73 16.509 0.73 16.509 Descamps, 05 B f 16.5045 0.86 16.5045 0.86 16.5045 Behrend, 07w B f 16.505046 16.505046 Bartczak, 14 93 Minerva M 5.982 0.20 M a 5.982 0.20 57.79 Marchis, 11 107∗ Camilla M 4.844 0.53 B a Marchis, 08 B a 4.8439 89.04 Marchis, 11w M a 1.550 Marsset, 16 M s 89.096 4.91 Pajuelo, 18 113 Amalthea B? 9.950 0.22 ? u Maley, 17 121 Hermione B 5.55128 0.62 B a Merline, 02 B a Marchis, 04 B a Marchis, 05 B a 5.55 61.97 Marchis, 11w 130 Elektra M 5.225 0.58 B a 5.22 126.2 Marchis, 08 M a Yang, 14 216 Kleopatra M 5.385 1.22 M a 5.38 Marchis, 08 243 Ida B 4.634 0.86 B a Belton, 94 279 Thule B? 23.896 0.10 B s 7.44 0.08 72.2 Sato, 15 283 Emma B 6.896 0.53 B a Merline, 03 B a 6.89 80.48 Marchis, 08 324 Bamberga B? 29.43 0.12 B s 29.458 0.06 71.0 Sato, 15 379 Huenna B 14.141 0.12 B a Margot, 03 B a 4.022 2102.
    [Show full text]
  • Ice & Stone 2020
    Ice & Stone 2020 WEEK 15: APRIL 5-11, 2020 Presented by The Earthrise Institute # 15 Authored by Alan Hale This week in history APRIL 5 6 7 8 9 10 11 APRIL 5, 1861: An amateur astronomer in New York, A.E. Thatcher, discovers a 9th-magnitude comet. Comet Thatcher was found to have an approximate orbital period of 415 years and is the parent comet of the Lyrid meteor shower, which peaks around April 22 each year. The Lyrids usually put on a modest display of less than 20 meteors per hour, but on occasion have produced much stronger displays, most recently in 1982. APRIL 5 6 7 8 9 10 11 APRIL 8, 1957: Comet Arend-Roland 1956h passes through perihelion at a heliocentric distance of 0.316 AU. This was one of the brighter comets of the mid-20th Century and is a future “Comet of the Week.” APRIL 8, 2024: The path of a total solar eclipse will cross north-central Mexico and the south-central and northeastern U.S. This may be my last, best chance to see an eclipse comet; I discuss these in a future “Special Topics” presentation. APRIL 5 6 7 8 9 10 11 APRIL 9, 1994: Radar bounce experiments conducted by the joint NASA/U.S. Defense Department Clementine spacecraft suggest the presence of water ice in permanently shadowed craters near the moon’s South Pole. This would be confirmed by NASA’sLunar Prospector mission in 1998. These experiments are discussed as part of a future “Special Topics” presentation. *There are no calendar entries for April 6 and 7.
    [Show full text]
  • Asteroid Impact & Deflection Assessment (AIDA)
    Asteroid Impact & Deflection Assessment (AIDA) Andrew F Cheng JHU/APL Cheryl Reed JHU/APL Andy Rivkin JHU/APL Andres Galvez ESA Ian Carnelli ESA Patrick Michel CNRS Stephan Ulamec DLR Jens Biele DLR Paul Abell JSC Brent Barbee GSFC Dan Mazanek LaRC Lance Benner JPL Approved for Public Release Mitigating the Asteroid Hazard § Defending Planet Earth: Near-Earth- Object Surveys and Hazard Mitigation Strategies (US National Research Council, 2010) q Civil defense q Slow push or pull q Kinetic impactors q Nuclear explosions § Space Mission Priorities for Near- Earth Object Risk Assessment and Reduction (ESA NEOMAP, 2004) q Don Quijote mission study 5/29/2012 2 ESA Don Quijote study § Don Quijote asteroid deflection mission studied by ESA in 2005-2007 § Two launches § Interceptor § Rendezvous § Not affordable 5/29/2012 3 Asteroid Mitigation • Target NEO Global Community Workshop in February 2011 (http://www.targetneo.org/) • International Workshop on Mitigation at the PDC in 2011 • JHU/APL, ESA and other participating NASA Centers started a joint Mitigation Demonstration Mission Study in 2012 q This has become AIDA ESA web site: Search web for “AIDA mission” 5/29/2012 4 AIDA Program Overview § Double Asteroid Redirection Test (DART) study q NASA HQ, GSFC, JSC, LaRC, JPL q Asteroid impact and deflection, cost under $150 M including launch § Asteroid Impact Mission (AIM) study q ESA HQ, CNRS, DLR q Impact test and characterization, cost under €150 M including launch AIDA = AIM + DART 5/29/2012 5 AIDA Asteroid Deflection Study § AIDA will send
    [Show full text]
  • AIDA: the Asteroid Impact & Deflection Assessment Mission
    EPSC Abstracts Vol. 8, EPSC2013-1043, 2013 European Planetary Science Congress 2013 EEuropeaPn PlanetarSy Science CCongress c Author(s) 2013 AIDA: The Asteroid Impact & Deflection Assessment Mission A. Galvez 1 ( email: [email protected]), I. Carnelli 1, P. Michel 2, A.F. Cheng 3, C. Reed 3, S. Ulamec4, J. Biele4, P. Abell5, R. Landis6. 1 European Space Agency HQ, Paris,2 Lagrange Laboratory, University of Nice-Sophia Antipolis, CNRS, Côte d’Azur Observatory, 3 Johns Hopkins University Applied Physics Laboratory, 4 DLR, Koeln, Germany, 5NASA JSC, Houston, USA, 6NASA HQ, USA Abstract involved an orbiter and an impactor spacecraft, with the orbiter arriving first, measuring the deflection by The Asteroid Impact and Deflection Assessment radio tracking, monitoring the impact and making (AIDA) mission, a joint effort of ESA, JHU/APL, additional characterization measurements. Unlike NASA, OCA, and DLR, is the first demonstration of Don Quijote, AIDA envisions an impactor spacecraft asteroid deflection and assessment via kinetic impact. to intercept the secondary member of a binary near- AIDA consists of two independent but mutually Earth asteroid, with additional ground-based supporting mission elements, one of which is the observations to measure the deflection. In the joint asteroid kinetic impactor and the other is the AIDA mission, DART combines with the ESA AIM characterization spacecraft. These two missions are, mission which will rendezvous with the asteroid. respectively, JHU/APL’s Double Asteroid Each of these missions has independent value, with Redirection Test (DART) and the European Space greatly increased return when combined. Both DART Agency’s Asteroid Investigation Mission (AIM) and AIM are low cost missions.
    [Show full text]
  • Robotic Asteroid Prospector (RAP) NASA Contract NNX12AR04G -- 9 July 2013, REV 12 Dec 2013 ©
    Phase I Final Report to NASA Innovative and Advanced Concepts (NIAC) Robotic Asteroid Prospector (RAP) NASA Contract NNX12AR04G -- 9 July 2013, REV 12 Dec 2013 © PI: Marc M. Cohen, Arch.D; Marc M. Cohen Architect P. C. Astrotecture™ http://www.astrotecture.com CoI for Mission and Spacecraft Design: Warren W. James, V Infinity Research LLC. CoI for Mining and Robotics: Kris Zacny, PhD, with Jack Craft and Philip Chu, Honeybee Robotics. Consultant for Mining Economics: Brad Blair, New Space Analytics LLC Table of Contents Abstract ............................................................................................................................. 5 Executive Summary ............................................................................................................ 6 1 Introduction ............................................................................................................... 10 1.1 Mineral Economics Strategy ............................................................................................................................ 10 1.2 Asteroids, Meteorites, and Metals ................................................................................................................. 10 1.2.1 Families of Metals ................................................................................................................................................ 10 1.2.2 Water from Carbonaceous Chondrites ....................................................................................................... 10 1.3
    [Show full text]
  • Annexe I : Description Des Services D’Observations Labellisés Liés À La Planétologie
    Annexe I : description des services d’observations labellisés liés à la planétologie Consultation BDD Service des éphémérides Type AA-ANO1 Coordination Intitulé OSU Directeur de l'OSU Responsable du SNO Email du responsable du SNO IMCCE Jacques LASKAR Jacques LASKAR [email protected] Partenaires Intitulé OSU Directeur de l'OSU Resp. du SNO dans l'OSU Email du resp. du SNO dans l'OSU Obs. Paris Claude CATALA OCA Thierry LANZ Agnès FIENGA [email protected] Description L'IMCCE a la responsabilité, sous l'égide du Bureau des longitudes, de produire et de diffuser les calendriers et éphémérides au niveau national. Cette fonction est assurée l'institut par son Service des éphémérides. Aussi celui-ci a) produit les publications et éditions annuelles tout comme les éphémérides en ligne, b) diffuse les éphémérides de divers corps du système solaire - naturels et artificiels, et de phénomènes célestes, c) assure la maintenance et la mise jour des bases de données, d) procure une expertise juridique aux tribunaux, e) procure des éphémérides et données la demande pour les services similaires (USA, Japon), les agences, les chercheurs, les laboratoires et les observatoires. Consultation BDD Gaia Type AA-ANO1, AA-ANO4 Coordination Intitulé OSU Directeur de l'OSU Responsable du SNO Email du responsable du SNO OCA Thierry LANZ François MIGNARD [email protected] Partenaires Intitulé OSU Directeur de l'OSU Resp. du SNO dans l'OSU Email du resp. du SNO dans l'OSU Obs. Paris Claude CATALA Frédéric ARENOU [email protected] IMCCE Jacques LASKAR Daniel HESTROFFER [email protected] OASU Marie Lise DUBERNET-TUCKEY Caroline SOUBIRAN [email protected] THETA Philippe ROUSSELOT Annie ROBIN [email protected] IAP Francis BERNARDEAU Brigitte ROCCA VOLMERANGE [email protected] ObAS Pierre-Alain DUC Jean-Louis HALBWACHS [email protected] Description Participation aux activités du Consortium DPAC (Data Processing and Analysis Consortium) pour la mission Gaia.
    [Show full text]
  • Mechanical Properties of Particles from the Surface of Asteroid 25143 Itokawa Safoura Tanbakouei1,2, Josep M
    A&A 629, A119 (2019) https://doi.org/10.1051/0004-6361/201935380 Astronomy & © ESO 2019 Astrophysics Mechanical properties of particles from the surface of asteroid 25143 Itokawa Safoura Tanbakouei1,2, Josep M. Trigo-Rodríguez1,2, Jordi Sort3,4, Patrick Michel5, Jürgen Blum6, Tomoki Nakamura7, and Iwan Williams8 1 Institute of Space Sciences (ICE-CSIC), Campus UAB, C/Can Magrans s/n, 08193 Bellaterra (Barcelona), Catalonia, Spain e-mail: [email protected] 2 Institut d’Estudis Espacials de Catalunya (IEEC), C/Gran Capità, 2-4, Ed. Nexus, desp. 201, 08034 Barcelona, Catalonia, Spain 3 Departament de Fisica, Universitat Autònoma de Barcelona, 08193 Bellaterra, Catalonia, Spain 4 Institució Catalana de Recerca i Estudis Avançats, Passeig Lluís Companys 23, 08010 Barcelona, Catalonia, Spain 5 Université Côte d’Azur, Observatoire de la Côte d’Azur, CNRS, Lagrange Laboratory, France 6 Institut für Geophysik und extraterrestrische Physik, Technische Universität Braunschweig, Mendelssohnstr. 3, 38106 Braunschweig, Germany 7 Department of Earth Science, Graduate School of Science, Tohoku University, Japan 8 School of Physics and Astronomy, Queen Mary, University of London, Mile End Rd. London E1 4NS, UK Received 28 February 2019 / Accepted 10 July 2019 ABSTRACT Aims. Asteroids have been exposed to impacts since their formation, and as a consequence their surfaces are covered by small parti- cles, pebbles, and boulders. The Japanese JAXA/ISAS Hayabusa mission collected micron-sized particles from the regolith of asteroid 25143 Itokawa. The study in terrestrial laboratories of these particles provides a scientific opportunity as their physical properties can be compared with those characteristic of chondritic meteorites that are often considered proxies of the building materials of potentially hazardous asteroids (PHAs).
    [Show full text]