Planetary Science Division Status Report
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Curriculum Vitae
DANTE S. LAURETTA Lunar and Planetary Laboratory Department of Planetary Sciences University of Arizona Tucson, AZ 85721-0092 Cell: (520) 609-2088 Email: [email protected] CHRONOLOGY OF EDUCATION Washington University, St. Louis, MO Dept. of Earth and Planetary Sciences Ph.D. in Earth and Planetary Sciences, 1997 Thesis: Theoretical and Experimental Studies of Fe-Ni-S, Be, and B Cosmochemistry Advisor: Bruce Fegley, Jr. University of Arizona, Tucson, AZ Depts. of Physics, Mathematics, and East Asian Studies B.S. in Physics and Mathematics, Cum Laude, 1993 B.A. in Oriental Studies (emphasis: Japanese), Cum Laude, 1993 CHRONOLOGY OF EMPLOYMENT Professor, Lunar and Planetary Laboratory, Dept. of Planetary Sciences, University of Arizona, Tucson, AZ; 2012 – present. Principal Investigator, OSIRIS-REx Asteroid Sample Return Mission, NASA New Frontiers Program, 2011 – present. Deputy Principal Investigator, OSIRIS-REx Asteroid Sample Return Mission, NASA New Frontiers Program, 2008 – 2011. Associate Professor, Lunar and Planetary Laboratory, Dept. of Planetary Sciences, University of Arizona, Tucson, AZ; 2006 – 2012. Assistant Professor, Lunar and Planetary Laboratory, Dept. of Planetary Sciences, University of Arizona, Tucson, AZ; 2001 – 2006. Associate Research Scientist, Dept. of Chemistry & Biochemistry, Arizona State University, Tempe, AZ; 1999 – 2001. Postdoctoral Research Associate, Dept. of Geology, Arizona State University, Tempe, AZ Primary project: Transmission electron microscopy of meteoritic minerals. Supervisor: Peter R. Buseck; Dates: 1997 – 1999. Research Assistant, Dept. of Earth and Planetary Sciences, Washington Univ., St. Louis, MO Primary project: Experimental studies of sulfide formation in the solar nebula. Advisor: Bruce Fegley, Jr.; Dates: 1993 – 1997. Research Intern, NASA Undergraduate Research Program, University of Arizona, Tucson, AZ Primary project: Development of a logic-based language for S.E.T.I. -
Deep Impact As a World Observatory Event Held in Brussels, Belgium, 7–10 August 2006
Other Astronomical News Report on the Workshop on Deep Impact as a World Observatory Event held in Brussels, Belgium, 7–10 August 2006 Hans Ulrich Käufl1 One of the spectacular deconvolved images from the Christiaan Sterken2 Deep Impact Spacecraft High Resolution Imager shown in the conference (courtesy Mike A’Hearn and the Deep Impact Team). This is a colour composite of an infrared, a green and a violet filter forced to av- 1 ESO erage grey. Note the blueish areas on the surface 2 Vrije Universiteit Brussel, Belgium close to the crater-like structure. Those were entirely unexpected. It is highly interesting to find out if those structures can be correlated with the jets which were meticulously monitored from ground-based ob- In the context of NASA’s Deep Impact servers worldwide. This aspect in the picture – en- space mission, Comet 9P/Tempel1 tirely unrelated to the impact plume – illustrates very well how comet research, apart from the impact has been at the focus of an unprece- experiment, will profit from the synergy of spacecraft dented worldwide long-term multi- data and the unprecedented worldwide coordinated wavelength observation campaign. The observing campaign. comet has been studied through its perihelion passage by various spacecraft including the Deep Impact mission it- self, HST, Spitzer, Rosetta, XMM and all To make full use of the global data set, a To inspire new ideas, it was very helpful major ground-based observatories in workshop bringing together observers and interesting to have Roberta Olson basically all wavelength bands used in across the electromagnetic spectrum and from the New York Historical Society, astronomy, i.e. -
Modelling Bennu's Crater Development
EPSC Abstracts Vol. 14, EPSC2020-442, 2020 https://doi.org/10.5194/epsc2020-442 Europlanet Science Congress 2020 © Author(s) 2021. This work is distributed under the Creative Commons Attribution 4.0 License. Modelling Bennu's Crater Development Peter Smith, Daniella DellaGiustina, Keara Burke, Dathon Golish, and Dante Lauretta University of Arizona, Planetary Sciences, Tucson, United States of America ([email protected]) Modeling Bennu’s Crater Development P.H. Smith (1), D.N. DellaGiustina (1), K.N. Burke (1), D.R. Golish (1), D. S. Lauretta (1) (1) Lunar and Planetary Laboratory, University of Arizona, USA ([email protected]) Introduction Several hundred craters have been identified and mapped on Bennu [1]. Their spectral properties have been studied using data from the MapCam instrument onboard the OSIRIS-REx spacecraft [2]. The crater frequency versus spectral slope across the wavelength range of 0.550 µm (v band) to 0.860 µm (x band) shows a skewed distribution varying from the median spectral slope of –0.17 micron–1 (x/v = 0.948) to a neutral or flat slope (x/v = 1.0). DellaGiustina et al. [2] attribute this trend to space weathering. They suggest that freshly formed craters are red, and as they age, they evolve to the bluish slope seen across the asteroidal surface. This abstract presents the results of an age model of Bennu’s craters in the size range of 1 to 10 m. Craters in this size range were selected as having likely been formed during the time that Bennu has orbited in near-Earth space. -
Size of Particles Ejected from an Artificial Impact Crater on Asteroid
A&A 647, A43 (2021) Astronomy https://doi.org/10.1051/0004-6361/202039777 & © K. Wada et al. 2021 Astrophysics Size of particles ejected from an artificial impact crater on asteroid 162173 Ryugu K. Wada1, K. Ishibashi1, H. Kimura1, M. Arakawa2, H. Sawada3, K. Ogawa2,4, K. Shirai2, R. Honda5, Y. Iijima3, T. Kadono6, N. Sakatani7, Y. Mimasu3, T. Toda3, Y. Shimaki3, S. Nakazawa3, H. Hayakawa3, T. Saiki3, Y. Takagi8, H. Imamura3, C. Okamoto2, M. Hayakawa3, N. Hirata9, and H. Yano3 1 Planetary Exploration Research Center, Chiba Institute of Technology, Narashino 275-0016, Japan e-mail: [email protected] 2 Department of Planetology, Kobe University, Kobe 657-8501, Japan 3 Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan 4 JAXA Space Exploration Center, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan 5 Department of Science and Technology, Kochi University, Kochi 780-8520, Japan 6 Department of Basic Sciences, University of Occupational and Environmental Health, Kitakyusyu 807-8555, Japan 7 Department of Physics, Rikkyo University, Tokyo 171-8501, Japan 8 Aichi Toho University, Nagoya 465-8515, Japan 9 School of Computer Science and Engineering, The University of Aizu, Aizu-Wakamatsu 965-8580, Japan Received 28 October 2020 / Accepted 26 January 2021 ABSTRACT A projectile accelerated by the Hayabusa2 Small Carry-on Impactor successfully produced an artificial impact crater with a final apparent diameter of 14:5 0:8 m on the surface of the near-Earth asteroid 162173 Ryugu on April 5, 2019. At the time of cratering, Deployable Camera 3 took± clear time-lapse images of the ejecta curtain, an assemblage of ejected particles forming a curtain-like structure emerging from the crater. -
+ 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 -
A Ballistics Analysis of the Deep Impact Ejecta Plume: Determining Comet Tempel 1’S Gravity, Mass, and Density
Icarus 190 (2007) 357–390 www.elsevier.com/locate/icarus A ballistics analysis of the Deep Impact ejecta plume: Determining Comet Tempel 1’s gravity, mass, and density James E. Richardson a,∗,H.JayMeloshb, Carey M. Lisse c, Brian Carcich d a Center for Radiophysics and Space Research, Cornell University, Ithaca, NY 14853, USA b Lunar and Planetary Laboratory, University of Arizona, Tucson, AZ 85721-0092, USA c Planetary Exploration Group, Space Department, Johns Hopkins University Applied Physics Laboratory, 11100 Johns Hopkins Road, Laurel, MD 20723, USA d Center for Radiophysics and Space Research, Cornell University, Ithaca, NY 14853, USA Received 31 March 2006; revised 8 August 2007 Available online 15 August 2007 Abstract − In July of 2005, the Deep Impact mission collided a 366 kg impactor with the nucleus of Comet 9P/Tempel 1, at a closing speed of 10.2 km s 1. In this work, we develop a first-order, three-dimensional, forward model of the ejecta plume behavior resulting from this cratering event, and then adjust the model parameters to match the flyby-spacecraft observations of the actual ejecta plume, image by image. This modeling exercise indicates Deep Impact to have been a reasonably “well-behaved” oblique impact, in which the impactor–spacecraft apparently struck a small, westward-facing slope of roughly 1/3–1/2 the size of the final crater produced (determined from initial ejecta plume geometry), and possessing an effective strength of not more than Y¯ = 1–10 kPa. The resulting ejecta plume followed well-established scaling relationships for cratering in a medium-to-high porosity target, consistent with a transient crater of not more than 85–140 m diameter, formed in not more than 250–550 s, for the case of Y¯ = 0 Pa (gravity-dominated cratering); and not less than 22–26 m diameter, formed in not less than 1–3 s, for the case of Y¯ = 10 kPa (strength-dominated cratering). -
EPOXI COMET ENCOUNTER FACT SHEET Nov
EPOXI COMET ENCOUNTER FACT SHEET Nov. 2, 2010 Quick Facts Flyby Spacecraft Dimensions: 3.3 meters (10.8 feet) long, 1.7 meters (5.6 feet) wide, and 2.3 meters (7.5 feet) high Weight: 601 kilograms (1,325 pounds) at launch, consisting of 517 kilograms (1,140 pounds) spacecraft and 84 kilograms (185 pounds) fuel. On 10/25/10 there was 4 kilograms (8.8 pounds) of fuel remaining. Power: 2.8-meter-by-2.8-meter (9-foot-by-9 foot) solar panel providing up to 750 watts, depending on distance from sun. Power storage via small, 16-amp- hourrechargeable nickel hydrogen battery Comet Hartley 2 Nucleus shape: Elongated Nucleus size (estimated): About 2.2 kilometers (1.4 miles) long Nucleus mass: Roughly 280 million metric tons Nucleus rotation period: About 18 hours Nucleus composition: Water ice, carbon dioxide ice, silicate dust Mission Launch: Jan. 12, 2005 Launch site: Cape Canaveral Air Force Station, Florida Launch vehicle: Delta II 7925 with Star 48 upper stage Impact with Tempel 1: 10:52 p.m. PDT July 3, 2005 (1:52 a.m. EDT July 4, 2005) Earth-comet distance at time of impact: 133.6 million kilometers (83 million miles) Total distance traveled by spacecraft from Earth to Tempel 1: 431 million kilometers (268 million miles) Flyby of Hartley 2: About 10 a.m. EDT or 7 a.m. PDT Nov. 4, 2010 Additional distance traveled by spacecraft to Hartley 2: About 4.6 billion kilometers (2.9 billion miles) Program Cost of Deep Impact: $267 million total (not including launch vehicle), consisting of $252 million spacecraft development and $15 million mission operations Cost of EPOXI extended mission: $42 million, for operations from 2007 to end of project at the end of fiscal year 2011. -
An Artificial Impact on the Asteroid (162173) Ryugu Formed a Crater in the Gravity-Dominated Regime M
An artificial impact on the asteroid (162173) Ryugu formed a crater in the gravity-dominated regime M. Arakawa, T. Saiki, K. Wada, K. Ogawa, T. Kadono, K. Shirai, H. Sawada, K. Ishibashi, R. Honda, N. Sakatani, et al. To cite this version: M. Arakawa, T. Saiki, K. Wada, K. Ogawa, T. Kadono, et al.. An artificial impact on the asteroid (162173) Ryugu formed a crater in the gravity-dominated regime. Science, American Association for the Advancement of Science, 2020, 368 (6486), pp.67-71. 10.1126/science.aaz1701. hal-02986191 HAL Id: hal-02986191 https://hal.archives-ouvertes.fr/hal-02986191 Submitted on 7 Jan 2021 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. Submitted Manuscript Title: An artificial impact on the asteroid 162173 Ryugu formed a crater in the gravity-dominated regime Authors: M. Arakawa1*, T. Saiki2, K. Wada3, K. Ogawa21,1, T. Kadono4, K. Shirai2,1, H. Sawada2, K. Ishibashi3, R. Honda5, N. Sakatani2, Y. Iijima2§, C. Okamoto1§, H. Yano2, Y. 5 Takagi6, M. Hayakawa2, P. Michel7, M. Jutzi8, Y. Shimaki2, S. Kimura9, Y. Mimasu2, T. Toda2, H. Imamura2, S. Nakazawa2, H. Hayakawa2, S. -
Planetary Science
Mission Directorate: Science Theme: Planetary Science Theme Overview Planetary Science is a grand human enterprise that seeks to discover the nature and origin of the celestial bodies among which we live, and to explore whether life exists beyond Earth. The scientific imperative for Planetary Science, the quest to understand our origins, is universal. How did we get here? Are we alone? What does the future hold? These overarching questions lead to more focused, fundamental science questions about our solar system: How did the Sun's family of planets, satellites, and minor bodies originate and evolve? What are the characteristics of the solar system that lead to habitable environments? How and where could life begin and evolve in the solar system? What are the characteristics of small bodies and planetary environments and what potential hazards or resources do they hold? To address these science questions, NASA relies on various flight missions, research and analysis (R&A) and technology development. There are seven programs within the Planetary Science Theme: R&A, Lunar Quest, Discovery, New Frontiers, Mars Exploration, Outer Planets, and Technology. R&A supports two operating missions with international partners (Rosetta and Hayabusa), as well as sample curation, data archiving, dissemination and analysis, and Near Earth Object Observations. The Lunar Quest Program consists of small robotic spacecraft missions, Missions of Opportunity, Lunar Science Institute, and R&A. Discovery has two spacecraft in prime mission operations (MESSENGER and Dawn), an instrument operating on an ESA Mars Express mission (ASPERA-3), a mission in its development phase (GRAIL), three Missions of Opportunities (M3, Strofio, and LaRa), and three investigations using re-purposed spacecraft: EPOCh and DIXI hosted on the Deep Impact spacecraft and NExT hosted on the Stardust spacecraft. -
NASA's Planetary Science Lunar Activities and Plans
NASA Lunar Science Activities James L. Green Planetary Science Division NASA Headquarters Washington DC 20546 [email protected] NASA’s Planetary Science Division (PSD) program encompasses a broad range of missions to many destinations in the solar system but the Earth’s Moon holds a special place in these efforts. Our planetary science missions are either strategic or openly competed through announcements of opportunity and are led by a principal investigator (PI). In exploring any particular solar system object, NASA has followed a general paradigm of “flyby, orbit, land, rove, and return.” This prescription has been followed most completely for investigations of the Moon and Mars. The Exploration Systems Mission Directorate (ESMD) will be launching the Lunar Reconnaissance Orbiter (LRO) in 2008 in preparation for manned missions to the Moon. LRO is a strategic mission with competed instrumentation to support exploration goals. After one year of LRO observations, ESMD will transition the spacecraft operations to the PSD for its prime science mission phase. The two competitive PI mission lines in the Planetary Science Division are called Discovery and New Frontiers, both of which have the potential to support Lunar missions. Currently there are three Phase-A studies in competition in the Discovery program which includes the Gravity Recovery and Interior Laboratory (GRAIL) mission by Maria Zuber (PI), MIT. The down-selection for Discovery will be announced later this year. GRAIL proposes to use high-quality gravity field mapping of the Moon to determine its interior structure. The New Frontiers program will next be in competition by late 2008 providing a potential opportunity for a sample return mission from the South Pole-Aitken basin. -
New Horizons 2 Alan Stern (Swri), Rick Binzel (MIT), Hal Levison
New Horizons 2 Alan Stern (SwRI), Rick Binzel (MIT), Hal Levison (SwRI), Rosaly Lopes (JPL), Bob Millis (Lowell Observatory), and Jeff Moore (NASA Ames) New Horizons is the inaugural mission in NASA’s New Frontiers program—a series of mid-sized planetary exploration projects. This mission was competitively selected in 2001 after a peer review competition between industry-university teams. The mission is on track toward a planned launch in January 2006—just over 6 months hence. The primary objective of New Horizons (NH) is to make the first reconnaissance of the solar system’s farthest planet, Pluto, its comparably sized satellite Charon. If an extended mission is approved, New Horizons may be able to also flyby a Kuiper Belt Object (KBOs) farther from the Sun. The exploration of the Kuiper Belt and Pluto-Charon was ranked as the highest new start priority for planetary exploration by the National Research Council’s recently completed (2002) Decadal Survey for Planetary Science. In accomplishing its goals, the mission is expected to reveal fundamental new insights into the nature of the outer solar system, the formation history of the planets, the workings of binary worlds, and the ancient repository of water and organic building blocks called the Kuiper Belt. Beyond its scientific ambitions, New Horizons is also breaking ground in lowering the cost of exploration of the outer solar system—for it is being built and launched for what are literally dimes on the dollar compared to deep outer solar system missions like Voyager, Galileo, and Cassini. The New Horizons spacecraft carries a suite of seven advanced, miniaturized instruments to obtain detailed imagery, mapping spectroscopy, thermal mapping, gravitational data, and in situ plasma composition, density, and energy sampling of the exotic, icy Pluto- Charon binary and a modest-sized (~50 km diameter) KBO. -
Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2
Space Sci Rev DOI 10.1007/s11214-016-0286-8 Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2 Tatsuaki Okada 1,2 · Tetsuya Fukuhara3 · Satoshi Tanaka1 · Makoto Taguchi3 · Takeshi Imamura4 · Takehiko Arai 1 · Hiroki Senshu5 · Yoshiko Ogawa6 · Hirohide Demura6 · Kohei Kitazato6 · Ryosuke Nakamura7 · Toru Kouyama7 · Tomohiko Sekiguchi8 · Sunao Hasegawa1 · Tsuneo Matsunaga9 · Takehiko Wada1 · Jun Takita2 · Naoya Sakatani1 · Yamato Horikawa10 · Ken Endo6 · Jörn Helbert11 · Thomas G. Müller12 · Axel Hagermann13 Received: 24 September 2015 / Accepted: 31 August 2016 © The Author(s) 2016. This article is published with open access at Springerlink.com Abstract The thermal infrared imager TIR onboard Hayabusa2 has been developed to in- vestigate thermo-physical properties of C-type, near-Earth asteroid 162173 Ryugu. TIR is one of the remote science instruments on Hayabusa2 designed to understand the nature of a volatile-rich solar system small body, but it also has significant mission objectives to pro- vide information on surface physical properties and conditions for sampling site selection B T. Okada [email protected] 1 Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, Japan 2 Graduate School of Science, The University of Tokyo, Bunkyo Tokyo, Japan 3 Rikkyo University, Tokyo, Japan 4 Graduate School of Frontiers Sciences, The University of Tokyo Kashiwa, Japan 5 Planetary Exploration Research Center, Chiba Institute of Technology, Narashino, Japan 6 Center