Solar System Science and Exploration
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Volcanic History of the Imbrium Basin: a Close-Up View from the Lunar Rover Yutu
Volcanic history of the Imbrium basin: A close-up view from the lunar rover Yutu Jinhai Zhanga, Wei Yanga, Sen Hua, Yangting Lina,1, Guangyou Fangb, Chunlai Lic, Wenxi Pengd, Sanyuan Zhue, Zhiping Hef, Bin Zhoub, Hongyu Ling, Jianfeng Yangh, Enhai Liui, Yuchen Xua, Jianyu Wangf, Zhenxing Yaoa, Yongliao Zouc, Jun Yanc, and Ziyuan Ouyangj aKey Laboratory of Earth and Planetary Physics, Institute of Geology and Geophysics, Chinese Academy of Sciences, Beijing 100029, China; bInstitute of Electronics, Chinese Academy of Sciences, Beijing 100190, China; cNational Astronomical Observatories, Chinese Academy of Sciences, Beijing 100012, China; dInstitute of High Energy Physics, Chinese Academy of Sciences, Beijing 100049, China; eKey Laboratory of Mineralogy and Metallogeny, Guangzhou Institute of Geochemistry, Chinese Academy of Sciences, Guangzhou 510640, China; fKey Laboratory of Space Active Opto-Electronics Technology, Shanghai Institute of Technical Physics, Chinese Academy of Sciences, Shanghai 200083, China; gThe Fifth Laboratory, Beijing Institute of Space Mechanics & Electricity, Beijing 100076, China; hXi’an Institute of Optics and Precision Mechanics, Chinese Academy of Sciences, Xi’an 710119, China; iInstitute of Optics and Electronics, Chinese Academy of Sciences, Chengdu 610209, China; and jInstitute of Geochemistry, Chinese Academy of Science, Guiyang 550002, China Edited by Mark H. Thiemens, University of California, San Diego, La Jolla, CA, and approved March 24, 2015 (received for review February 13, 2015) We report the surface exploration by the lunar rover Yutu that flows in Mare Imbrium was obtained only by remote sensing from landed on the young lava flow in the northeastern part of the orbit. On December 14, 2013, Chang’e-3 successfully landed on the Mare Imbrium, which is the largest basin on the nearside of the young and high-Ti lava flow in the northeastern Mare Imbrium, Moon and is filled with several basalt units estimated to date from about 10 km south from the old low-Ti basalt unit (Fig. -
A Summary of the Unified Lunar Control Network 2005 and Lunar Topographic Model B. A. Archinal, M. R. Rosiek, R. L. Kirk, and B
A Summary of the Unified Lunar Control Network 2005 and Lunar Topographic Model B. A. Archinal, M. R. Rosiek, R. L. Kirk, and B. L. Redding U. S. Geological Survey, 2255 N. Gemini Drive, Flagstaff, AZ 86001, USA, [email protected] Introduction: We have completed a new general unified lunar control network and lunar topographic model based on Clementine images. This photogrammetric network solution is the largest planetary control network ever completed. It includes the determination of the 3-D positions of 272,931 points on the lunar surface and the correction of the camera angles for 43,866 Clementine images, using 546,126 tie point measurements. The solution RMS is 20 µm (= 0.9 pixels) in the image plane, with the largest residual of 6.4 pixels. We are now documenting our solution [1] and plan to release the solution results soon [2]. Previous Networks: In recent years there have been two generally accepted lunar control networks. These are the Unified Lunar Control Network (ULCN) and the Clementine Lunar Control Network (CLCN), both derived by M. Davies and T. Colvin at RAND. The original ULCN was described in the last major publication about a lunar control network [3]. Images for this network are from the Apollo, Mariner 10, and Galileo missions, and Earth-based photographs. The CLCN was derived from Clementine images and measurements on Clementine 750-nm images. The purpose of this network was to determine the geometry for the Clementine Base Map [4]. The geometry of that mosaic was used to produce the Clementine UVVIS digital image model [5] and the Near-Infrared Global Multispectral Map of the Moon from Clementine [6]. -
Modeling and Adjustment of THEMIS IR Line Scanner Camera Image Measurements
Modeling and Adjustment of THEMIS IR Line Scanner Camera Image Measurements by Brent Archinal USGS Astrogeology Team 2255 N. Gemini Drive Flagstaff, AZ 86001 [email protected] As of 2004 December 9 Version 1.0 Table of Contents 1. Introduction 1.1. General 1.2. Conventions 2. Observations Equations and Their Partials 2.1. Line Scanner Camera Specific Modeling 2.2. Partials for New Parameters 2.2.1. Orientation Partials 2.2.2. Spatial Partials 2.2.3. Partials of the observations with respect to the parameters 2.2.4. Parameter Weighting 3. Adjustment Model 4. Implementation 4.1. Input/Output Changes 4.1.1. Image Measurements 4.1.2. SPICE Data 4.1.3. Program Control (Parameters) Information 4.2. Computational Changes 4.2.1. Generation of A priori Information 4.2.2. Partial derivatives 4.2.3. Solution Output 5. Testing and Near Term Work 6. Future Work Acknowledgements References Useful web sites Appendix I - Partial Transcription of Colvin (1992) Documentation Appendix II - HiRISE Sensor Model Information 1. Introduction 1.1 General The overall problem we’re solving is that we want to be able to set up the relationships between the coordinates of arbitrary physical points in space (e.g. ground points) and their coordinates on line scanner (or “pushbroom”) camera images. We then want to do a least squares solution in order to come up with consistent camera orientation and position information that represents these relationships accurately. For now, supported by funding from the NASA Critical Data Products initiative (for 2003 September to 2005 August), we will concentrate on handling the THEMIS IR camera system (Christensen et al., 2003). -
Honorarable Chair, Distinguished Delegates, It Is an Honour for Me to Address the Scientific and Technical Subcommittee of COPUO
February 2020 United Nations Committee on the Peaceful Uses of Outer Space 57th Session of COPUOS STSC Austria, Vienna, 3 - 14 February 2020 Statement of the International Astronautical Federation (IAF) Honorarable Chair, Distinguished Delegates, It is an honour for me to address the Scientific and Technical Subcommittee of COPUOS in my capacity as IAF Vice- President for Relations with International Organizations and representing the newly elected IAF President, Prof. Pascale Ehrenfreund, who could not join us today. Distinguished Delegates, Since its creation in 1951 the IAF has pursued its main goal to provide a platform for organizations, communities and individuals, active and enthusiastic about space, to meet, share knowledge and connect with each other in a cooperative spirit. Following its mission of Connecting @ll Space People, the IAF continuously seeks to deepen international cooperation worldwide by encouraging the advancement of knowledge about space and fostering dialogue between scientists, engineers, policy makers and all other space actors for the benefit of humanity. Please allow me to briefly highlight some of the IAF’s manifold past activities and also give you an outlook on some upcoming events: IAF Secretariat - 100 Avenue de Suffren - 75015 Paris, France T: +33 (0)1 45 67 42 60 - E: [email protected] - W: www.iafastro.org Non-profit organisation established under the French Law of 1 July 1901 The 70th International Astronautical Congress held in Washington, D.C., United States was an outstanding success with more than 6.800 participants coming from over 80 countries, for an intense week of events, meetings, and discoveries. The Congress started with the Honorable Mike Pence, Vice President of the United States, confirming the USA plans to go forward to the Moon and land the first woman and the next man on the Lunar surface by 2024. -
An Overview of Hayabusa2 Mission and Asteroid 162173 Ryugu
Asteroid Science 2019 (LPI Contrib. No. 2189) 2086.pdf AN OVERVIEW OF HAYABUSA2 MISSION AND ASTEROID 162173 RYUGU. S. Watanabe1,2, M. Hira- bayashi3, N. Hirata4, N. Hirata5, M. Yoshikawa2, S. Tanaka2, S. Sugita6, K. Kitazato4, T. Okada2, N. Namiki7, S. Tachibana6,2, M. Arakawa5, H. Ikeda8, T. Morota6,1, K. Sugiura9,1, H. Kobayashi1, T. Saiki2, Y. Tsuda2, and Haya- busa2 Joint Science Team10, 1Nagoya University, Nagoya 464-8601, Japan ([email protected]), 2Institute of Space and Astronautical Science, JAXA, Japan, 3Auburn University, U.S.A., 4University of Aizu, Japan, 5Kobe University, Japan, 6University of Tokyo, Japan, 7National Astronomical Observatory of Japan, Japan, 8Research and Development Directorate, JAXA, Japan, 9Tokyo Institute of Technology, Japan, 10Hayabusa2 Project Summary: The Hayabusa2 mission reveals the na- Combined with the rotational motion of the asteroid, ture of a carbonaceous asteroid through a combination global surveys of Ryugu were conducted several times of remote-sensing observations, in situ surface meas- from ~20 km above the sub-Earth point (SEP), includ- urements by rovers and a lander, an active impact ex- ing global mapping from ONC-T (Fig. 1) and TIR, and periment, and analyses of samples returned to Earth. scan mapping from NIRS3 and LIDAR. Descent ob- Introduction: Asteroids are fossils of planetesi- servations covering the equatorial zone were performed mals, building blocks of planetary formation. In partic- from 3-7 km altitudes above SEP. Off-SEP observa- ular carbonaceous asteroids (or C-complex asteroids) tions of the polar regions were also conducted. Based are expected to have keys identifying the material mix- on these observations, we constructed two types of the ing in the early Solar System and deciphering the global shape models (using the Structure-from-Motion origin of water and organic materials on Earth [1]. -
Space Diplomacy & Making “Space for Women” Leaders
Space Diplomacy & Making “Space for Women” Leaders UNITED NATIONS EXPERT MEETING ON ‘SPACE FOR WOMEN” 4th – 6th October 2017 New York, USA Namira Salim Founder & Executive Chairperson Space Trust Space Diplomacy & Making “Space for Women” Leaders A New Space Age Commercialization or Democratization of Space Opens the Final Frontier to All Sectors 10% 37% 14% 2016 $329 Billion Global Space Economy Total Annual Revenue 39% Non US Govt Space Budgets US Govt Space Budgets Comm. Space P + S Comm. Infrastructure & Industry Space Report 2016 - Space Foundation Encouraging Public- Triggering a New Complex Space Private Partnerships Space Economy Environment From the Edge of Space to Low Earth Orbit, to the Moon, Mars & Beyond Space Diplomacy & Making “Space for Women” Leaders SPACE DIPLOMACY & MAKING “SPACE FOR WOMEN” LEADERS Our NewSpace Age or “Democratisation of Space” provides low-cost access to space and makes space "Inclusive for All." Spacefaring & New Space Nations expanding cooperation in Low Earth Orbit, to asteroids, the Moon, Mars & beyond via human & robotic missions Deep Space Habitats & colonies on Mars will Evolve Humans into Inter- Planetary Ambassadors As the final frontier opens to all sectors, why not open space to world leaders and above all, women in global leadership roles to find innovative solutions for a peaceful world? Raise awareness for Space Diplomacy on the institutional level Advocate & encourage Women Leaders in Political Sectors & Female Heads of State to exercise space diplomacy in an increasingly complex -
Mini-RF: Imaging Radars for Exploring the Lunar Poles
Mini-RF: Imaging Radars for Exploring the Lunar Poles Ben Bussey, Paul Spudis, Keith Raney, Helene Winters JHU/APL Stu Nozette, Chris Lichtenberg, Bill Marinelli NAWC 1 Mini-RF Organization, Science and Resource Evaluation Objectives • Mini-RF is a suite of radar instruments funded by NASA (SOMD & ESMD) and DoD. • Search for areas near the lunar poles that have the anomalous radar reflectivity signatures (high radar albedo and Circular Polarization Ratios) that differentiate volumetric water-ice deposits from more typical lunar surfaces • Map the morphology of permanently dark regions near the poles 2 Search for Ice • The case for water-ice can be resolved only if robust and repeatable data of the lunar polar regions support that conclusion. This rigorous standard can be met only by a dedicated polar-orbiting radar. • Mini-RF will use a unique hybrid polarity architecture to look for ice deposits • Transmit circular polarization (e.g. right-circular polarization RCP) • Receive coherent orthogonal polarizations • Derive Stokes parameters of the received signal • Use Stokes parameters to reconstruct and investigate the nature of the backscatter field. Distinguish between surface (roughness) and volume (ice) scattering 3 Top-level Radar Overview Parameter Chandrayaan-1 LRO • Frequency S-band S-band and X-band • Polarization Tx RCP Rx H & V • Scatterometry S-band (none) • Imager Regional maps Site-specific selections • Resolution (m/pixel) 75 75, 7.5 azimuth x 15 range • Looks 16 16 or 8 • Swath (km) 8 6 or 4 • Altitude (km) 100 50 • Incidence -
Space Sector Brochure
SPACE SPACE REVOLUTIONIZING THE WAY TO SPACE SPACECRAFT TECHNOLOGIES PROPULSION Moog provides components and subsystems for cold gas, chemical, and electric Moog is a proven leader in components, subsystems, and systems propulsion and designs, develops, and manufactures complete chemical propulsion for spacecraft of all sizes, from smallsats to GEO spacecraft. systems, including tanks, to accelerate the spacecraft for orbit-insertion, station Moog has been successfully providing spacecraft controls, in- keeping, or attitude control. Moog makes thrusters from <1N to 500N to support the space propulsion, and major subsystems for science, military, propulsion requirements for small to large spacecraft. and commercial operations for more than 60 years. AVIONICS Moog is a proven provider of high performance and reliable space-rated avionics hardware and software for command and data handling, power distribution, payload processing, memory, GPS receivers, motor controllers, and onboard computing. POWER SYSTEMS Moog leverages its proven spacecraft avionics and high-power control systems to supply hardware for telemetry, as well as solar array and battery power management and switching. Applications include bus line power to valves, motors, torque rods, and other end effectors. Moog has developed products for Power Management and Distribution (PMAD) Systems, such as high power DC converters, switching, and power stabilization. MECHANISMS Moog has produced spacecraft motion control products for more than 50 years, dating back to the historic Apollo and Pioneer programs. Today, we offer rotary, linear, and specialized mechanisms for spacecraft motion control needs. Moog is a world-class manufacturer of solar array drives, propulsion positioning gimbals, electric propulsion gimbals, antenna positioner mechanisms, docking and release mechanisms, and specialty payload positioners. -
Enhanced Gravity Tractor Technique for Planetary Defense
4th IAA Planetary Defense Conference – PDC 2015 13-17 April 2015, Frascati, Roma, Italy IAA-PDC-15-04-11 ENHANCED GRAVITY TRACTOR TECHNIQUE FOR PLANETARY DEFENSE Daniel D. Mazanek(1), David M. Reeves(2), Joshua B. Hopkins(3), Darren W. Wade(4), Marco Tantardini(5), and Haijun Shen(6) (1)NASA Langley Research Center, Mail Stop 462, 1 North Dryden Street, Hampton, VA, 23681, USA, 1-757-864-1739, (2) NASA Langley Research Center, Mail Stop 462, 1 North Dryden Street, Hampton, VA, 23681, USA, 1-757-864-9256, (3)Lockheed Martin Space Systems Company, Mail Stop H3005, PO Box 179, Denver, CO 80201, USA, 1-303- 971-7928, (4)Lockheed Martin Space Systems Company, Mail Stop S8110, PO Box 179, Denver, CO 80201, USA, 1-303-977-4671, (5)Independent, via Tibaldi 5, Cremona, Italy, +393381003736, (6)Analytical Mechanics Associates, Inc., 21 Enterprise Parkway, Suite 300, Hampton, VA 23666, USA, 1-757-865-0000, Keywords: enhanced gravity tractor, in-situ mass augmentation, asteroid and comet deflection, planetary defense, low-thrust, high-efficiency propulsion, gravitational attraction, robotic mass collection Abstract Given sufficient warning time, Earth-impacting asteroids and comets can be deflected with a variety of different “slow push/pull” techniques. The gravity tractor is one technique that uses the gravitational attraction of a rendezvous spacecraft to the impactor and a low-thrust, high-efficiency propulsion system to provide a gradual velocity change and alter its trajectory. An innovation to this technique, known as the Enhanced Gravity Tractor (EGT), uses mass collected in-situ to augment the mass of the spacecraft, thereby greatly increasing the gravitational force between the objects. -
Stardust Sample Return
National Aeronautics and Space Administration Stardust Sample Return Press Kit January 2006 www.nasa.gov Contacts Merrilee Fellows Policy/Program Management (818) 393-0754 NASA Headquarters, Washington DC Agle Stardust Mission (818) 393-9011 Jet Propulsion Laboratory, Pasadena, Calif. Vince Stricherz Science Investigation (206) 543-2580 University of Washington, Seattle, Wash. Contents General Release ............................................................................................................... 3 Media Services Information ……………………….................…………….................……. 5 Quick Facts …………………………………………..................………....…........…....….. 6 Mission Overview …………………………………….................……….....……............…… 7 Recovery Timeline ................................................................................................ 18 Spacecraft ………………………………………………..................…..……...........……… 20 Science Objectives …………………………………..................……………...…..........….. 28 Why Stardust?..................…………………………..................………….....………............... 31 Other Comet Missions .......................................................................................... 33 NASA's Discovery Program .................................................................................. 36 Program/Project Management …………………………........................…..…..………...... 40 1 2 GENERAL RELEASE: NASA PREPARES FOR RETURN OF INTERSTELLAR CARGO NASA’s Stardust mission is nearing Earth after a 2.88 billion mile round-trip journey -
Asteroid Retrieval Feasibility Study
Asteroid Retrieval Feasibility Study 2 April 2012 Prepared for the: Keck Institute for Space Studies California Institute of Technology Jet Propulsion Laboratory Pasadena, California 1 2 Authors and Study Participants NAME Organization E-Mail Signature John Brophy Co-Leader / NASA JPL / Caltech [email protected] Fred Culick Co-Leader / Caltech [email protected] Co -Leader / The Planetary Louis Friedman [email protected] Society Carlton Allen NASA JSC [email protected] David Baughman Naval Postgraduate School [email protected] NASA ARC/Carnegie Mellon Julie Bellerose [email protected] University Bruce Betts The Planetary Society [email protected] Mike Brown Caltech [email protected] Michael Busch UCLA [email protected] John Casani NASA JPL [email protected] Marcello Coradini ESA [email protected] John Dankanich NASA GRC [email protected] Paul Dimotakis Caltech [email protected] Harvard -Smithsonian Center for Martin Elvis [email protected] Astrophysics Ian Garrick-Bethel UCSC [email protected] Bob Gershman NASA JPL [email protected] Florida Institute for Human and Tom Jones [email protected] Machine Cognition Damon Landau NASA JPL [email protected] Chris Lewicki Arkyd Astronautics [email protected] John Lewis University of Arizona [email protected] Pedro Llanos USC [email protected] Mark Lupisella NASA GSFC [email protected] Dan Mazanek NASA LaRC [email protected] Prakhar Mehrotra Caltech [email protected] -
How the Current View of the Air and Space Environment
AU/ACSC/006/1998-04 AIR COMMAND AND STAFF COLLEGE AIR UNIVERSITY HOW THE CURRENT VIEW OF THE AIR AND SPACE ENVIRONMENT INFLUENCES DEVELOPMENT OF MILITARY SPACE FORCES by Lyndon S. Anderson, Major, USAF Stephen M. Rothstein, Major, USAF A Research Report Submitted to the Faculty In Partial Fulfillment of the Graduation Requirements Advisor: Lt Col Theresa R. Clark Maxwell Air Force Base, Alabama April 1998 Disclaimer The views expressed in this academic research paper are those of the author(s) and do not reflect the official policy or position of the US government or the Department of Defense. In accordance with Air Force Instruction 51-303, it is not copyrighted, but is the property of the United States government. ii Contents Page DISCLAIMER................................................................................................................ ii LIST OF TABLES.......................................................................................................... v PREFACE...................................................................................................................... vi ABSTRACT ................................................................................................................ viii INTRODUCTION .......................................................................................................... 1 THE CURRENT PARADIGM........................................................................................ 4 Describing the Current Paradigm..............................................................................