Lunar Occultation Observer (LOCO)
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Surface Characteristics of Transneptunian Objects and Centaurs from Photometry and Spectroscopy
Barucci et al.: Surface Characteristics of TNOs and Centaurs 647 Surface Characteristics of Transneptunian Objects and Centaurs from Photometry and Spectroscopy M. A. Barucci and A. Doressoundiram Observatoire de Paris D. P. Cruikshank NASA Ames Research Center The external region of the solar system contains a vast population of small icy bodies, be- lieved to be remnants from the accretion of the planets. The transneptunian objects (TNOs) and Centaurs (located between Jupiter and Neptune) are probably made of the most primitive and thermally unprocessed materials of the known solar system. Although the study of these objects has rapidly evolved in the past few years, especially from dynamical and theoretical points of view, studies of the physical and chemical properties of the TNO population are still limited by the faintness of these objects. The basic properties of these objects, including infor- mation on their dimensions and rotation periods, are presented, with emphasis on their diver- sity and the possible characteristics of their surfaces. 1. INTRODUCTION cally with even the largest telescopes. The physical char- acteristics of Centaurs and TNOs are still in a rather early Transneptunian objects (TNOs), also known as Kuiper stage of investigation. Advances in instrumentation on tele- belt objects (KBOs) and Edgeworth-Kuiper belt objects scopes of 6- to 10-m aperture have enabled spectroscopic (EKBOs), are presumed to be remnants of the solar nebula studies of an increasing number of these objects, and signifi- that have survived over the age of the solar system. The cant progress is slowly being made. connection of the short-period comets (P < 200 yr) of low We describe here photometric and spectroscopic studies orbital inclination and the transneptunian population of pri- of TNOs and the emerging results. -
New Views of the Moon Enabled by Combined Remotely Sensed and Lunar Sample Data Sets, a Lunar Initiative
New Views of the Moon Enabled by Combined Remotely Sensed and Lunar Sample Data Sets, A Lunar Initiative Using the hand tool on your Reader, click on the links below to view that particular section of the proposal. Proposal Summary Scientific/Technical/Management Objectives and Expected Significance Background and Impact Approach and Methodology: The Role of Integration in Fundamental Problems of Lunar Geoscience Workshop 2: New Views of the Moon II: Understanding the Moon Through the Integration of Diverse Datasets. Abstract Volume and Subsequent Publications Statement of Relevance Work Plan Potential Workshop (2000): Thermal and Magmatic Evolution of the Moon Potential Workshop (2001): Early Lunar Differentiation, Core Formation, Effects of Early Planetesimal Impacts, and the Origin of the Moon’s Global Asymmetry Potential Workshop (2002): Selection of Sites for Future Sample Return Capstone Publication Timeline for the New Views of the Moon Initiative Personnel: Initiative Management and Proposal Management References Facilities: The LPI Appendix 1. Workshop on New Views of the Moon: Integrated Remotely Sensed, Geophysical, and Sample Datasets. List of presentations Appendix 2. LPSC 30 (1999) special sessions related to the Lunar Initiative. List of presentations (oral and poster) Appendix 3. Lunar Initiative Steering Committee Web Note: This is the text of a proposal submitted on behalf of the Lunar Science Community to support ongoing workshops and activities associated with the CAPTEM Lunar Initiative. It was submitted in May, 1999, in response to the ROSS 99 NRA, which solicits such proposals to be submitted to the relevant research programs. This proposal was submitted jointly to Cosmo- chemistry and Planetary Geology and Geophysics. -
Atlas V Launches LRO/LCROSS Mission Overview
Atlas V Launches LRO/LCROSS Mission Overview Atlas V 401 Cape Canaveral Air Force Station, FL Space Launch Complex-41 AV-020/LRO/LCROSS United Launch Alliance is proud to be a part of the Lunar Reconnaissance Orbiter (LRO) and the Lunar Crater Observation and Sensing Satellite (LCROSS) mission with the National Aeronautics and Space Administration (NASA). The LRO/LCROSS mission marks the sixteenth Atlas V launch and the seventh flight of an Atlas V 401 configuration. LRO/LCROSS is a dual-spacecraft (SC) launch. LRO is a lunar orbiter that will investigate resources, landing sites, and the lunar radiation environment in preparation for future human missions to the Moon. LCROSS will search for the presence of water ice that may exist on the permanently shadowed floors of lunar polar craters. The LCROSS mission will use two Lunar Kinetic Impactors, the inert Centaur upper stage and the LCROSS SC itself, to produce debris plumes that may reveal the presence of water ice under spectroscopic analysis. My thanks to the entire Atlas team for its dedication in bringing LRO/LCROSS to launch, and to NASA for selecting Atlas for this ground-breaking mission. Go Atlas, Go Centaur, Go LRO/LCROSS! Mark Wilkins Vice President, Atlas Product Line Atlas V Launch History Flight Config. Mission Mission Date AV-001 401 Eutelsat Hotbird 6 21 Aug 2002 AV-002 401 HellasSat 13 May 2003 AV-003 521 Rainbow 1 17 Jul 2003 AV-005 521 AMC-16 17 Dec 2004 AV-004 431 Inmarsat 4-F1 11 Mar 2005 AV-007 401 Mars Reconnaissance Orbiter 12 Aug 2005 AV-010 551 Pluto New Horizons 19 Jan 2006 AV-008 411 Astra 1KR 20 Apr 2006 AV-013 401 STP-1 08 Mar 2007 AV-009 401 NROL-30 15 Jun 2007 AV-011 421 WGS SV-1 10 Oct 2007 AV-015 401 NROL-24 10 Dec 2007 AV-006 411 NROL-28 13 Mar 2008 AV-014 421 ICO G1 14 Apr 2008 AV-016 421 WGS-2 03 Apr 2009 Payload Fairing Number of Solid Atlas V Size (meters) Rocket Boosters Flight/Configuration Key AV-XXX ### Number of Centaur Engines 3-digit Tail Number 3-digit Configuration Number LRO Overview LRO is the first mission in NASA’s planned return to the Moon. -
Exploration of the Kuiper Belt by High-Precision Photometric Stellar Occultations: First Results F
Exploration of the Kuiper Belt by High-Precision Photometric Stellar Occultations: First Results F. Roques, A. Doressoundiram, V. Dhillon, T. Marsh, S. Bickerton, J. J. Kavelaars, M. Moncuquet, M. Auvergne, I. Belskaya, M. Chevreton, et al. To cite this version: F. Roques, A. Doressoundiram, V. Dhillon, T. Marsh, S. Bickerton, et al.. Exploration of the Kuiper Belt by High-Precision Photometric Stellar Occultations: First Results. Astronomical Journal, Amer- ican Astronomical Society, 2006, 132, pp.819-822. 10.1086/505623. hal-00640050 HAL Id: hal-00640050 https://hal.archives-ouvertes.fr/hal-00640050 Submitted on 10 Nov 2011 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. The Astronomical Journal, 132:819Y822, 2006 August # 2006. The American Astronomical Society. All rights reserved. Printed in U.S.A. EXPLORATION OF THE KUIPER BELT BY HIGH-PRECISION PHOTOMETRIC STELLAR OCCULTATIONS: FIRST RESULTS F. Roques,1,2 A. Doressoundiram,1 V. Dhillon,3 T. Marsh,4 S. Bickerton,5,6 J. J. Kavelaars,5 M. Moncuquet,1 M. Auvergne,1 I. Belskaya,7 M. Chevreton,1 F. Colas,1 A. Fernandez,1 A. Fitzsimmons,8 J. Lecacheux,1 O. Mousis,9 S. -
Protons in the Near Lunar Wake Observed by the SARA Instrument on Board Chandrayaan-1
FUTAANA ET AL. PROTONS IN DEEP WAKE NEAR MOON 1 Protons in the Near Lunar Wake Observed by the SARA 2 Instrument on Board Chandrayaan-1 3 Y. Futaana, 1 S. Barabash, 1 M. Wieser, 1 M. Holmström, 1 A. Bhardwaj, 2 M. B. Dhanya, 2 R. 4 Sridharan, 2 P. Wurz, 3 A. Schaufelberger, 3 K. Asamura 4 5 --- 6 Y. Futaana, Swedish Institute of Space Physics, Box 812, Kiruna, SE-98128, Sweden. 7 ([email protected]) 8 9 10 1 Swedish Institute of Space Physics, Box 812, Kiruna, SE-98128, Sweden 11 2 Space Physics Laboratory, Vikram Sarabhai Space Center, Trivandrum 695 022, India 12 3 Physikalisches Institut, University of Bern, Sidlerstrasse 5, CH-3012 Bern, Switzerland 13 4 Institute of Space and Astronautical Science, 3-1-1 Yoshinodai, Sagamihara, Japan 14 Index Terms 15 6250 Moon 16 5421 Interactions with particles and fields 17 2780 Magnetospheric Physics: Solar wind interactions with unmagnetized bodies 18 7807 Space Plasma Physics: Charged particle motion and acceleration 19 Abstract 20 Significant proton fluxes were detected in the near wake region of the Moon by an ion mass 21 spectrometer on board Chandrayaan-1. The energy of these nightside protons is slightly higher than 22 the energy of the solar wind protons. The protons are detected close to the lunar equatorial plane at 23 a 140˚ solar zenith angle, i.e., ~50˚ behind the terminator at a height of 100 km. The protons come 24 from just above the local horizon, and move along the magnetic field in the solar wind reference 25 frame. -
Global Mapping of Elemental Abundance on Lunar Surface by SELENE Gamma-Ray Spectrometer
Lunar and Planetary Science XXXVI (2005) 2092.pdf Global Mapping of elemental abundance on lunar surface by SELENE gamma-ray spectrometer. 1M. -N. Kobayashi, 1A. A. Berezhnoy, 6C. d’Uston, 1M. Fujii, 1N. Hasebe, 3T. Hiroishi, 4H. Kaneko, 1T. Miyachi, 5K. Mori, 6S. Maurice, 4M. Nakazawa, 3K. Narasaki, 1O. Okudaira, 1E. Shibamura, 2T. Takashima, 1N. Yamashita, 1Advanced Research Institute of Sci.& Eng., Waseda Univ., 3-4-1, Okubo, Shinjuku-ku, Tokyo, 169-8555, Japan, (masa- [email protected]), 2Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Sagamihara, Kanagawa, 229-8510, 3Niihama Works, Sumitomo Heavy Industry Ltd., Niihama, Ehime, Japan, Moriya Works, 4Meisei Electric Co., Ltd., 3-249-1, Yuri-ga-oka, Moriya-shi, Ibaraki, 302-0192, 5Clear Pulse Co., 6-25-17, Chuo, Ohta-ku, Tokyo, Japan, 143-0024, 6Centre d’Etude Spatiale des Rayonnements, CNRS/UPS, Colonel Roche, B.P 4346, France. Introduction: Elemental composition on the sur- face of a planet is very important information for solv- ing the origin and the evolution of the planet and also very necessary for understanding the origin and the evolution of solar system. Planetary gamma-ray spec- troscopy is extremely powerful approach for the ele- mental composition measurement. Gamma-ray spec- trometer (GRS) will be on board SELENE, advanced lunar polar orbiter, and employ a large-volume Ge detector of 252cc as the main detector [1]. SELENE GRS is, therefore, approximately twice more sensitiv- ity than Lunar Prospector GRS, four times more sensi- Figure 1: The schematic drawing of SELENE Gamma- tive than APOLLO GRS. -
Mission Design for the Lunar Reconnaissance Orbiter
AAS 07-057 Mission Design for the Lunar Reconnaissance Orbiter Mark Beckman Goddard Space Flight Center, Code 595 29th ANNUAL AAS GUIDANCE AND CONTROL CONFERENCE February 4-8, 2006 Sponsored by Breckenridge, Colorado Rocky Mountain Section AAS Publications Office, P.O. Box 28130 - San Diego, California 92198 AAS-07-057 MISSION DESIGN FOR THE LUNAR RECONNAISSANCE ORBITER † Mark Beckman The Lunar Reconnaissance Orbiter (LRO) will be the first mission under NASA’s Vision for Space Exploration. LRO will fly in a low 50 km mean altitude lunar polar orbit. LRO will utilize a direct minimum energy lunar transfer and have a launch window of three days every two weeks. The launch window is defined by lunar orbit beta angle at times of extreme lighting conditions. This paper will define the LRO launch window and the science and engineering constraints that drive it. After lunar orbit insertion, LRO will be placed into a commissioning orbit for up to 60 days. This commissioning orbit will be a low altitude quasi-frozen orbit that minimizes stationkeeping costs during commissioning phase. LRO will use a repeating stationkeeping cycle with a pair of maneuvers every lunar sidereal period. The stationkeeping algorithm will bound LRO altitude, maintain ground station contact during maneuvers, and equally distribute periselene between northern and southern hemispheres. Orbit determination for LRO will be at the 50 m level with updated lunar gravity models. This paper will address the quasi-frozen orbit design, stationkeeping algorithms and low lunar orbit determination. INTRODUCTION The Lunar Reconnaissance Orbiter (LRO) is the first of the Lunar Precursor Robotic Program’s (LPRP) missions to the moon. -
March 21–25, 2016
FORTY-SEVENTH LUNAR AND PLANETARY SCIENCE CONFERENCE PROGRAM OF TECHNICAL SESSIONS MARCH 21–25, 2016 The Woodlands Waterway Marriott Hotel and Convention Center The Woodlands, Texas INSTITUTIONAL SUPPORT Universities Space Research Association Lunar and Planetary Institute National Aeronautics and Space Administration CONFERENCE CO-CHAIRS Stephen Mackwell, Lunar and Planetary Institute Eileen Stansbery, NASA Johnson Space Center PROGRAM COMMITTEE CHAIRS David Draper, NASA Johnson Space Center Walter Kiefer, Lunar and Planetary Institute PROGRAM COMMITTEE P. Doug Archer, NASA Johnson Space Center Nicolas LeCorvec, Lunar and Planetary Institute Katherine Bermingham, University of Maryland Yo Matsubara, Smithsonian Institute Janice Bishop, SETI and NASA Ames Research Center Francis McCubbin, NASA Johnson Space Center Jeremy Boyce, University of California, Los Angeles Andrew Needham, Carnegie Institution of Washington Lisa Danielson, NASA Johnson Space Center Lan-Anh Nguyen, NASA Johnson Space Center Deepak Dhingra, University of Idaho Paul Niles, NASA Johnson Space Center Stephen Elardo, Carnegie Institution of Washington Dorothy Oehler, NASA Johnson Space Center Marc Fries, NASA Johnson Space Center D. Alex Patthoff, Jet Propulsion Laboratory Cyrena Goodrich, Lunar and Planetary Institute Elizabeth Rampe, Aerodyne Industries, Jacobs JETS at John Gruener, NASA Johnson Space Center NASA Johnson Space Center Justin Hagerty, U.S. Geological Survey Carol Raymond, Jet Propulsion Laboratory Lindsay Hays, Jet Propulsion Laboratory Paul Schenk, -
Abstracts of the 50Th DDA Meeting (Boulder, CO)
Abstracts of the 50th DDA Meeting (Boulder, CO) American Astronomical Society June, 2019 100 — Dynamics on Asteroids break-up event around a Lagrange point. 100.01 — Simulations of a Synthetic Eurybates 100.02 — High-Fidelity Testing of Binary Asteroid Collisional Family Formation with Applications to 1999 KW4 Timothy Holt1; David Nesvorny2; Jonathan Horner1; Alex B. Davis1; Daniel Scheeres1 Rachel King1; Brad Carter1; Leigh Brookshaw1 1 Aerospace Engineering Sciences, University of Colorado Boulder 1 Centre for Astrophysics, University of Southern Queensland (Boulder, Colorado, United States) (Longmont, Colorado, United States) 2 Southwest Research Institute (Boulder, Connecticut, United The commonly accepted formation process for asym- States) metric binary asteroids is the spin up and eventual fission of rubble pile asteroids as proposed by Walsh, Of the six recognized collisional families in the Jo- Richardson and Michel (Walsh et al., Nature 2008) vian Trojan swarms, the Eurybates family is the and Scheeres (Scheeres, Icarus 2007). In this theory largest, with over 200 recognized members. Located a rubble pile asteroid is spun up by YORP until it around the Jovian L4 Lagrange point, librations of reaches a critical spin rate and experiences a mass the members make this family an interesting study shedding event forming a close, low-eccentricity in orbital dynamics. The Jovian Trojans are thought satellite. Further work by Jacobson and Scheeres to have been captured during an early period of in- used a planar, two-ellipsoid model to analyze the stability in the Solar system. The parent body of the evolutionary pathways of such a formation event family, 3548 Eurybates is one of the targets for the from the moment the bodies initially fission (Jacob- LUCY spacecraft, and our work will provide a dy- son and Scheeres, Icarus 2011). -
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. -
Appulses of Jupiter and Saturn
IN ORIGINAL FORM PUBLISHED IN: arXiv:(side label) [physics.pop-ph] Sternzeit 46, No. 1+2 / 2021 (ISSN: 0721-8168) Date: 6th May 2021 Appulses of Jupiter and Saturn Joachim Gripp, Emil Khalisi Sternzeit e.V., Kiel and Heidelberg, Germany e-mail: gripp or khalisi ...[at]sternzeit-online[dot]de Abstract. The latest conjunction of Jupiter and Saturn occurred at an optical distance of 6 arc minutes on 21 December 2020. We re-analysed all encounters of these two planets between -1000 and +3000 CE, as the extraordinary ones (< 10′) take place near the line of nodes every 400 years. An occultation of their discs did not and will not happen within the historical time span of ±5,000 years around now. When viewed from Neptune though, there will be an occultation in 2046. Keywords: Jupiter-Saturn conjunction, Appulse, Trigon, Occultation. Introduction reason is due to Earth’s orbit: while Jupiter and Saturn are locked in a 5:2-mean motion resonance, the Earth does not The slowest naked-eye planets Jupiter and Saturn made an join in. For very long periods there could be some period- impressive encounter in December 2020. Their approaches icity, however, secular effects destroy a cycle, e.g. rotation have been termed “Great Conjunctions” in former times of the apsides and changes in eccentricity such that we are and they happen regularly every ≈20 years. Before the left with some kind of “semi-periodicity”. discovery of the outer ice giants these classical planets rendered the longest known cycle. The separation at the instant of conjunction varies up to 1 degree of arc, but the Close Encounters latest meeting was particularly tight since the planets stood Most pass-bys of Jupiter and Saturn are not very spectac- closer than at any other occasion for as long as 400 years. -
The Lunar Dust-Plasma Environment Is Crucial
TheThe LunarLunar DustDust --PlasmaPlasma EnvironmentEnvironment Timothy J. Stubbs 1,2 , William M. Farrell 2, Jasper S. Halekas 3, Michael R. Collier 2, Richard R. Vondrak 2, & Gregory T. Delory 3 [email protected] Lunar X-ray Observatory(LXO)/ Magnetosheath Explorer (MagEX) meeting, Hilton Garden Inn, October 25, 2007. 1 University of Maryland, Baltimore County 2 NASA Goddard Space Flight Center 3 University of California, Berkeley TheThe ApolloApollo AstronautAstronaut ExperienceExperience ofof thethe LunarLunar DustDust --PlasmaPlasma EnvironmentEnvironment “… one of the most aggravating, restricting facets of lunar surface exploration is the dust and its adherence to everything no matter what kind of material, whether it be skin, suit material, metal, no matter what it be and it’s restrictive friction-like action to everything it gets on. ” Eugene Cernan, Commander Apollo 17. EvidenceEvidence forfor DustDust AboveAbove thethe LunarLunar SurfaceSurface Horizon glow from forward scattered sunlight • Dust grains with radius of 5 – 6 m at about 10 to 30 cm from the surface, where electrostatic and gravitational forces balance. • Horizon glow ~10 7 too bright to be explained by micro-meteoroid- generated ejecta [Zook et al., 1995]. Composite image of morning and evening of local western horizon [Criswell, 1973]. DustDust ObservedObserved atat HighHigh AltitudesAltitudes fromfrom OrbitOrbit Schematic of situation consistent with Apollo 17 observations [McCoy, 1976]. Lunar dust at high altitudes (up to ~100 km). 0.1 m-scale dust present Gene Cernan sketches sporadically (~minutes). [McCoy and Criswell, 1974]. InIn --SituSitu EvidenceEvidence forfor DustDust TransportTransport Terminators Berg et al. [1976] Apollo 17 Lunar Ejecta and Meteorites (LEAM) experiment. PossiblePossible DustyDusty HorizonHorizon GlowGlow seenseen byby ClementineClementine StarStar Tracker?Tracker? Above: image of possible horizon glow above the lunar surface.