The Poles of the Moon
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The Surrender Software
Scientific image rendering for space scenes with the SurRender software Scientific image rendering for space scenes with the SurRender software R. Brochard, J. Lebreton*, C. Robin, K. Kanani, G. Jonniaux, A. Masson, N. Despré, A. Berjaoui Airbus Defence and Space, 31 rue des Cosmonautes, 31402 Toulouse Cedex, France [email protected] *Corresponding Author Abstract The autonomy of spacecrafts can advantageously be enhanced by vision-based navigation (VBN) techniques. Applications range from manoeuvers around Solar System objects and landing on planetary surfaces, to in -orbit servicing or space debris removal, and even ground imaging. The development and validation of VBN algorithms for space exploration missions relies on the availability of physically accurate relevant images. Yet archival data from past missions can rarely serve this purpose and acquiring new data is often costly. Airbus has developed the image rendering software SurRender, which addresses the specific challenges of realistic image simulation with high level of representativeness for space scenes. In this paper we introduce the software SurRender and how its unique capabilities have proved successful for a variety of applications. Images are rendered by raytracing, which implements the physical principles of geometrical light propagation. Images are rendered in physical units using a macroscopic instrument model and scene objects reflectance functions. It is specially optimized for space scenes, with huge distances between objects and scenes up to Solar System size. Raytracing conveniently tackles some important effects for VBN algorithms: image quality, eclipses, secondary illumination, subpixel limb imaging, etc. From a user standpoint, a simulation is easily setup using the available interfaces (MATLAB/Simulink, Python, and more) by specifying the position of the bodies (Sun, planets, satellites, …) over time, complex 3D shapes and material surface properties, before positioning the camera. -
EPSC2012-280 2012 European Planetary Science Congress 2012 Eeuropeapn Planetarsy Science Ccongress C Author(S) 2012
EPSC Abstracts Vol. 7 EPSC2012-280 2012 European Planetary Science Congress 2012 EEuropeaPn PlanetarSy Science CCongress c Author(s) 2012 A Simulation of exosphere of Ceres Ruby Lin Tu (1), Wing-Huen Ip(1,2,3) and Yung-Ching Wang (3) (1) Institute of Space Science, National Central University, Taiwan, (2) Institute of Astronomy, National Central University, Taiwan, (3) Space Science Institute, Macau University Science and Technology, Macau Abstract For the purpose of tracing the ballistic trajectories of water molecules on Ceres’ surface, we have to After Vesta, the NASA Dawn spacecraft will visit the produce a surface temperature map by omitting the largest asteroid Ceres, to carry out in-depth topographic variations and the presence of impact observations of its surface morphology and craters. Our model solves the heat conduction mineralogical composition. We examine different equation by taking account of the energy balance source mechanisms of a possible surface-bounded condition at the surface boundary and the lower exosphere composed of water molecules and other boundary condition (with dT/dz=0) into account. In species. Our preliminary assessment is that solar between the heat diffusion equation is solved by wind interaction and meteoroid impact are not using the Crank-Nicolson finite difference routine adequate because of the large injection speed of the gas at production relative to the surface escape velocity of Ceres. One potential source is a low-level (1) outgassing effect from its subsurface due to thermal sublimation. In this work, the scenario of building up a tenuous exosphere by ballistic transport and the eventual recycling of the water molecules to the polar cold trap is described. -
Qiao Et Al., Sosigenes Pit Crater Age 1/51
Qiao et al., Sosigenes pit crater age 1 2 The role of substrate characteristics in producing anomalously young crater 3 retention ages in volcanic deposits on the Moon: Morphology, topography, 4 sub-resolution roughness and mode of emplacement of the Sosigenes Lunar 5 Irregular Mare Patch (IMP) 6 7 Le QIAO1,2,*, James W. HEAD2, Long XIAO1, Lionel WILSON3, and Josef D. 8 DUFEK4 9 1Planetary Science Institute, School of Earth Sciences, China University of 10 Geosciences, Wuhan 430074, China. 11 2Department of Earth, Environmental and Planetary Sciences, Brown University, 12 Providence, RI 02912, USA. 13 3Lancaster Environment Centre, Lancaster University, Lancaster LA1 4YQ, UK. 14 4School of Earth and Atmospheric Sciences, Georgia Institute of Technology, Atlanta, 15 Georgia 30332, USA. 16 *Corresponding author E-mail: [email protected] 17 18 19 20 Key words: Lunar/Moon, Sosigenes, irregular mare patches, mare volcanism, 21 magmatic foam, lava lake, dike emplacement 22 23 24 25 1/51 Qiao et al., Sosigenes pit crater age 26 Abstract: Lunar Irregular Mare Patches (IMPs) are comprised of dozens of small, 27 distinctive and enigmatic lunar mare features. Characterized by their irregular shapes, 28 well-preserved state of relief, apparent optical immaturity and few superposed impact 29 craters, IMPs are interpreted to have been formed or modified geologically very 30 recently (<~100 Ma; Braden et al. 2014). However, their apparent relatively recent 31 formation/modification dates and emplacement mechanisms are debated. We focus in 32 detail on one of the major IMPs, Sosigenes, located in western Mare Tranquillitatis, 33 and dated by Braden et al. -
Ices on Mercury: Chemistry of Volatiles in Permanently Cold Areas of Mercury’S North Polar Region
Icarus 281 (2017) 19–31 Contents lists available at ScienceDirect Icarus journal homepage: www.elsevier.com/locate/icarus Ices on Mercury: Chemistry of volatiles in permanently cold areas of Mercury’s north polar region ∗ M.L. Delitsky a, , D.A. Paige b, M.A. Siegler c, E.R. Harju b,f, D. Schriver b, R.E. Johnson d, P. Travnicek e a California Specialty Engineering, Pasadena, CA b Dept of Earth, Planetary and Space Sciences, University of California, Los Angeles, CA c Planetary Science Institute, Tucson, AZ d Dept of Engineering Physics, University of Virginia, Charlottesville, VA e Space Sciences Laboratory, University of California, Berkeley, CA f Pasadena City College, Pasadena, CA a r t i c l e i n f o a b s t r a c t Article history: Observations by the MESSENGER spacecraft during its flyby and orbital observations of Mercury in 2008– Received 3 January 2016 2015 indicated the presence of cold icy materials hiding in permanently-shadowed craters in Mercury’s Revised 29 July 2016 north polar region. These icy condensed volatiles are thought to be composed of water ice and frozen Accepted 2 August 2016 organics that can persist over long geologic timescales and evolve under the influence of the Mercury Available online 4 August 2016 space environment. Polar ices never see solar photons because at such high latitudes, sunlight cannot Keywords: reach over the crater rims. The craters maintain a permanently cold environment for the ices to persist. Mercury surface ices magnetospheres However, the magnetosphere will supply a beam of ions and electrons that can reach the frozen volatiles radiolysis and induce ice chemistry. -
Project Selene: AIAA Lunar Base Camp
Project Selene: AIAA Lunar Base Camp AIAA Space Mission System 2019-2020 Virginia Tech Aerospace Engineering Faculty Advisor : Dr. Kevin Shinpaugh Team Members : Olivia Arthur, Bobby Aselford, Michel Becker, Patrick Crandall, Heidi Engebreth, Maedini Jayaprakash, Logan Lark, Nico Ortiz, Matthew Pieczynski, Brendan Ventura Member AIAA Number Member AIAA Number And Signature And Signature Faculty Advisor 25807 Dr. Kevin Shinpaugh Brendan Ventura 1109196 Matthew Pieczynski 936900 Team Lead/Operations Logan Lark 902106 Heidi Engebreth 1109232 Structures & Environment Patrick Crandall 1109193 Olivia Arthur 999589 Power & Thermal Maedini Jayaprakash 1085663 Robert Aselford 1109195 CCDH/Operations Michel Becker 1109194 Nico Ortiz 1109533 Attitude, Trajectory, Orbits and Launch Vehicles Contents 1 Symbols and Acronyms 8 2 Executive Summary 9 3 Preface and Introduction 13 3.1 Project Management . 13 3.2 Problem Definition . 14 3.2.1 Background and Motivation . 14 3.2.2 RFP and Description . 14 3.2.3 Project Scope . 15 3.2.4 Disciplines . 15 3.2.5 Societal Sectors . 15 3.2.6 Assumptions . 16 3.2.7 Relevant Capital and Resources . 16 4 Value System Design 17 4.1 Introduction . 17 4.2 Analytical Hierarchical Process . 17 4.2.1 Longevity . 18 4.2.2 Expandability . 19 4.2.3 Scientific Return . 19 4.2.4 Risk . 20 4.2.5 Cost . 21 5 Initial Concept of Operations 21 5.1 Orbital Analysis . 22 5.2 Launch Vehicles . 22 6 Habitat Location 25 6.1 Introduction . 25 6.2 Region Selection . 25 6.3 Locations of Interest . 26 6.4 Eliminated Locations . 26 6.5 Remaining Locations . 27 6.6 Chosen Location . -
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. -
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. -
Planning a Mission to the Lunar South Pole
Lunar Reconnaissance Orbiter: (Diviner) Audience Planning a Mission to Grades 9-10 the Lunar South Pole Time Recommended 1-2 hours AAAS STANDARDS Learning Objectives: • 12A/H1: Exhibit traits such as curiosity, honesty, open- • Learn about recent discoveries in lunar science. ness, and skepticism when making investigations, and value those traits in others. • Deduce information from various sources of scientific data. • 12E/H4: Insist that the key assumptions and reasoning in • Use critical thinking to compare and evaluate different datasets. any argument—whether one’s own or that of others—be • Participate in team-based decision-making. made explicit; analyze the arguments for flawed assump- • Use logical arguments and supporting information to justify decisions. tions, flawed reasoning, or both; and be critical of the claims if any flaws in the argument are found. • 4A/H3: Increasingly sophisticated technology is used Preparation: to learn about the universe. Visual, radio, and X-ray See teacher procedure for any details. telescopes collect information from across the entire spectrum of electromagnetic waves; computers handle Background Information: data and complicated computations to interpret them; space probes send back data and materials from The Moon’s surface thermal environment is among the most extreme of any remote parts of the solar system; and accelerators give planetary body in the solar system. With no atmosphere to store heat or filter subatomic particles energies that simulate conditions in the Sun’s radiation, midday temperatures on the Moon’s surface can reach the stars and in the early history of the universe before 127°C (hotter than boiling water) whereas at night they can fall as low as stars formed. -
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. -
(Unin)Habitable? Runaway Greenhouse
GEOS 22060/ GEOS 32060 / ASTR 45900 What makes a planet (unin)habitable? Runaway greenhouse Lecture 8 Tuesday 30 April 2019 Logiscs • Homework 1 and Homework 2 are graded • Homework 3 will be issued on Wed or Thu and due on Fri 10 • Total number of homeworks will be 6 (hopefully 7) • Midterm feedback form results: Course outline Founda6ons (1-2 weeks) • Earth history • HZ concept, atmospheric science essenEals • Post-Hadean Earth system Principles – how are habitable planets ini6ated and sustained? (4-5 weeks) • Volale supply, volale escape TODAY • Runaway greenhouse, moist greenhouse • Long-term climate evoluEon • Specifics (2.5 weeks) • Hyperthermals on Earth Earth science • Early Mars • Oceans within ice-covered moons • Exoplanetary systems e.g. TRAPPIST-1 system planetary science Lecture 7 wrap-up • Energy-limit: XUV driven escape more-likely- than-not sculpts the exoplanet radius-period distribuEon (‘photo-evaporaon valley’) • Diffusion limit: what regulates H loss from Venus, Earth and Mars today • Impact erosion – giant impacts and planetesimal impacts Wrap-up: impact erosion Nuclear tests Hydrocode Terrestrial impact craters Two-stage gas gun Formaon of Earth-sized planets involves giant (oligarchic) impacts. Masses of resulEng planets (Earths) * = giant impacts The output underlying this plot was generated by C. Cossou. The Moon-forming Simula8on intended to impact was not reproduce “typical” the last big impact Kepler system of short-period, on Earth, but it was 8ghtly-packed inner planets the last Eme that Earth hit another planet. The atmosphere-loss escape efficiency of giant impacts is set by the ground-moEon speed Schlichng & Mukhopadhay 2018 Ocean removal by giant impacts? (Ocean vaporizaon != ocean removal) Simulaons suggest that the Moon- forming impact was marginally able to remove any pre-exisEng Earth ocean 2 Qs ~ ve for oligarchic impact Stewart et al. -
Water Loss from Terrestrial Planets with CO2-Rich Atmospheres
Water loss from terrestrial planets with CO2-rich atmospheres R. D. Wordsworth Department of the Geophysical Sciences, University of Chicago, 60637 IL, USA [email protected] and R. T. Pierrehumbert Department of the Geophysical Sciences, University of Chicago, 60637 IL, USA ABSTRACT Water photolysis and hydrogen loss from the upper atmospheres of terrestrial planets is of fundamental importance to climate evolution but remains poorly understood in general. Here we present a range of calculations we performed to study the dependence of water loss rates from terrestrial planets on a range of atmospheric and external parameters. We show that CO2 can only cause sig- nificant water loss by increasing surface temperatures over a narrow range of conditions, with cooling of the middle and upper atmosphere acting as a bottle- neck on escape in other circumstances. Around G-stars, efficient loss only occurs on planets with intermediate CO2 atmospheric partial pressures (0.1 to 1 bar) that receive a net flux close to the critical runaway greenhouse limit. Because G-star total luminosity increases with time but XUV/UV luminosity decreases, this places strong limits on water loss for planets like Earth. In contrast, for a CO2-rich early Venus, diffusion limits on water loss are only important if clouds caused strong cooling, implying that scenarios where the planet never had surface liquid water are indeed plausible. Around M-stars, water loss is primarily a func- arXiv:1306.3266v2 [astro-ph.EP] 12 Oct 2013 tion of orbital distance, with planets that absorb less flux than ∼ 270 W m−2 (global mean) unlikely to lose more than one Earth ocean of H2O over their lifetimes unless they lose all their atmospheric N2/CO2 early on.