Lunar Exploration Timeline
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Quantitative Planetary Image Analysis Via Machine Learning
Tina Memo No. 2013-008 External, PhD Thesis, University of Manchester Quantitative Planetary Image Analysis via Machine Learning. Paul Tar Last updated 25 / 09 / 2014 Centre for Imaging Sciences, Medical School, University of Manchester, Stopford Building, Oxford Road, Manchester, M13 9PT. Quantitative Planetary Image Analysis via Machine Learning A thesis submitted to the University of Manchester for the degree of PhD in the faculty of Engineering and Physical Sciences 2014 Paul D. Tar School of Earth, Atmospheric and Environmental Sciences 2 Contents 1 Introduction 19 1.1 Theriseofimagingfromspace. ...... 19 1.1.1 Historicalimages ............................... 20 1.1.2 Contemporaryimages . 20 1.1.3 Futureimages.................................. 21 1.2 Sciencecase ..................................... .. 22 1.2.1 Lunarscience .................................. 22 1.2.2 Martianscience ................................ 22 1.3 Imageinterpretation ............................. ..... 23 1.3.1 Manualanalysis................................ 24 1.3.2 Automatedanalysis.............................. 24 1.4 Measurements.................................... .. 25 1.4.1 Quantitative measurements and The Scientific Method . .......... 26 1.4.2 Theroleofstatistics . ... 27 1.4.3 Assumptionsandapproximations . .... 29 1.5 Argumentforquantitativeautomation . ........ 30 1.6 Criteriaforaquantitativesystem . ......... 31 1.7 Thesisoutline ................................... ... 32 2 Literature Review 35 2.1 Representations ................................ -
Prescriptions for Excellence in Health Care a Collaboration Between Jefferson School of Population Health and Lilly Usa, Llc
PRESCRIPTIONS FOR EXCELLENCE IN HEALTH CARE A COLLABORATION BETWEEN JEFFERSON SCHOOL OF POPULATION HEALTH AND LILLY USA, LLC ISSUE 23 | WINTER 2015 EDITORIAL TABLE OF CONTENTS ACOs Due for Their Annual Checkup David B. Nash, MD, MBA A Message from Lilly: Opportunities, Uncertainty Loom in 2015 for the Editor-in-Chief Health Exchange Marketplace Ryan Urgo, MPP ....................................................2 As 2013 drew to a close, Premier with more than 190,000 physicians Healthcare Alliance predicted and other health care professionals Biography of a New ACO Joel Port, FACHE .............................................4 that participation in accountable participating.2 Although the care organizations (ACOs) would number of Medicare ACOs has Evolving Health Care Models and double in 2014 as a result of more grown more rapidly than the the Impact on Value and Quality providers developing core ACO number of non-Medicare ACOs, Bruce Perkins ...................................................6 capabilities.1 Premier’s forecast 46-52 million Americans (15%- Employers and Accountable Care was made on the basis of its 18% of the total population) are Organizations: A Good Marriage? survey of 115 senior executives patients in organizations with ACO Laurel Pickering, MPH .....................................9 that revealed a growing trend in arrangements with at least 1 payer.2 high-risk population management, coupled with reductions in cost The next question is, are ACOs and increases in health care quality doing what they are designed to do and patient satisfaction. Of those (ie, improving quality and lowering who responded: costs)? Although it is far too early to draw conclusions, the Centers • More than 75% reported for Medicare & Medicaid Services Prescriptions for Excellence in Health that they were integrating (CMS) has begun to release Care is brought to Population Health clinical and claims data to financial and quality outcomes. -
Lunar Orbiter Photographic Atlas of the Near Side of the Moon Charles J
Lunar Orbiter Photographic Atlas of the Near Side of the Moon Charles J. Byrne Lunar Orbiter Photographic Atlas of the Near Side of the Moon Charles J. Byrne Image Again Middletown, NJ USA Cover illustration: Earth-based photograph of the full Moon from the “Consolidated Lunar Atlas” on the Website of the Lunar and Planetary Institute. British Library Cataloging-in-Publication Data Byrne, Charles J., 1935– Lunar Orbiter photographic atlas of the near side of the Moon 1. Lunar Orbiter (Artificial satellite) 2. Moon–Maps 3. Moon–Photographs from space I. Title 523.3 0223 ISBN 1852338865 Library of Congress Cataloging-in-Publication Data Byrne, Charles J., 1935– Lunar Orbiter photographic atlas of the near side of the Moon : with 619 figures / Charles J. Byrne. p. cm. Includes bibliographical references and index. ISBN 1-85233-886-5 (acid-free paper) 1. Moon–Maps. 2. Moon–Photographs from space. 3. Moon–Remote-sensing images. 4. Lunar Orbiter (Artificial satellite) I. Title. G1000.3.B9 2005 523.3 022 3–dc22 2004045006 Additional material to this book can be downloaded from http://extras.springer.com. ISBN 1-85233-886-5 Printed on acid-free paper. © 2005 Springer-Verlag London Limited Apart from any fair dealing for the purposes of research or private study, or criticism, or review, as permitted under the Copyright, Designs and Patents Act 1988, this publication may only be repro- duced, stored or transmitted, in any form or by any means, with the prior permission in writing of the publishers, or in the case of reprographic reproduction in accordance with the terms of licenses issued by the Copyright Licensing Agency. -
Conceptual Human-System Interface Design for a Lunar Access Vehicle
Conceptual Human-System Interface Design for a Lunar Access Vehicle Mary Cummings Enlie Wang Cristin Smith Jessica Marquez Mark Duppen Stephane Essama Massachusetts Institute of Technology* Prepared For Draper Labs Award #: SC001-018 PI: Dava Newman HAL2005-04 September, 2005 http://halab.mit.edu e-mail: [email protected] *MIT Department of Aeronautics and Astronautics, Cambridge, MA 02139 TABLE OF CONTENTS 1 INTRODUCTION..................................................................................................... 1 1.1 THE GENERAL FRAMEWORK................................................................................ 1 1.2 ORGANIZATION.................................................................................................... 2 2 H-SI BACKGROUND AND MOTIVATION ........................................................ 3 2.1 APOLLO VS. LAV H-SI........................................................................................ 3 2.2 APOLLO VS. LUNAR ACCESS REQUIREMENTS ...................................................... 4 3 THE LAV CONCEPTUAL PROTOTYPE............................................................ 5 3.1 HS-I DESIGN ASSUMPTIONS ................................................................................ 5 3.2 THE CONCEPTUAL PROTOTYPE ............................................................................ 6 3.3 LANDING ZONE (LZ) DISPLAY............................................................................. 8 3.3.1 LZ Display Introduction................................................................................. -
Rideshare and the Orbital Maneuvering Vehicle: the Key to Low-Cost Lagrange-Point Missions
SSC15-II-5 Rideshare and the Orbital Maneuvering Vehicle: the Key to Low-cost Lagrange-point Missions Chris Pearson, Marissa Stender, Christopher Loghry, Joe Maly, Valentin Ivanitski Moog Integrated Systems 1113 Washington Avenue, Suite 300, Golden, CO, 80401; 303 216 9777, extension 204 [email protected] Mina Cappuccio, Darin Foreman, Ken Galal, David Mauro NASA Ames Research Center PO Box 1000, M/S 213-4, Moffett Field, CA 94035-1000; 650 604 1313 [email protected] Keats Wilkie, Paul Speth, Trevor Jackson, Will Scott NASA Langley Research Center 4 West Taylor Street, Mail Stop 230, Hampton, VA, 23681; 757 864 420 [email protected] ABSTRACT Rideshare is a well proven approach, in both LEO and GEO, enabling low-cost space access through splitting of launch charges between multiple passengers. Demand exists from users to operate payloads at Lagrange points, but a lack of regular rides results in a deficiency in rideshare opportunities. As a result, such mission architectures currently rely on a costly dedicated launch. NASA and Moog have jointly studied the technical feasibility, risk and cost of using an Orbital Maneuvering Vehicle (OMV) to offer Lagrange point rideshare opportunities. This OMV would be launched as a secondary passenger on a commercial rocket into Geostationary Transfer Orbit (GTO) and utilize the Moog ESPA secondary launch adapter. The OMV is effectively a free flying spacecraft comprising a full suite of avionics and a propulsion system capable of performing GTO to Lagrange point transfer via a weak stability boundary orbit. In addition to traditional OMV ’tug’ functionality, scenarios using the OMV to host payloads for operation at the Lagrange points have also been analyzed. -
Apollo 11 Lunar Landing Mission Press Kit, Part 2
-lOl- The ascent stage engine compartment is formed by two beams running across the lower midsection deck and mated to the fore and aft bulkheads. Systems located in the midsection include the LM guidance computer, the power and servo assembly, ascent engine propellant tanks, RCS pro- pellant tanks, the environmental control system, and the waste management section. A tunnel ring atop the ascent stage meshes with the command module docking latch assemblies. During docking, the CM docking ring and latches are aligned by the LM drogue and the CSM probe. The dockingtunnel extends downward into the midsection 16 inches (40 cm). The tunnel is B2 inches (0.81 cm) in dia- meter and Is used for crew transfer between the CSM and LM. The upper hatch on the inboard end of the docking tunnel hinges downward and cannot be opened with the LM pressurized and u_docked. A thermal and mlcrometeoroid shield of multiple layers of mylar and a single thickness of thin aluminum skin encases the entire ascent stage structure. Descent Stase The descent stage consists of a cruciform load-carrylng structure of two pairs of parallel beams, upper and lower decks, and enclosure bulkheads -- all of conventional skln-and-strlnger aluminum alloy construction. The center compartment houses the descent engine, and descent propellant tanks are housed in the four square bays around the engine. The descent stage measures i0 feet 7 inches high by 14 feet 1 inch in diameter. Four-legged truss outriggers mounted on the ends of each pair of beams serve as SLA attach points and as "knees" for the landing gear main struts. -
Lunar Orbiter Ii
NASA CONTRACTOR NASA CR-883 REPORT LUNAR ORBITER II Photographic Mission Summary Prepared by THE BOEING COMPANY Seattle, Wash. for Langley Research Center NATIONAl AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • OCTOBER 1967 THE CRATER COPERNICUS - Photo taken by NASA-Boeing Lunar Orbiter II, November 23, 1966,00:05:42 GMT, from a distance of 150 miles. NASA CR-883 LUNAR ORBITER II Photographic Mission Summary Distribution of this report is provided in the interest of information exchange. Responsibility for the contents resides in the author or organization that prepared it. Issued by Originator as Document No. D2-100752-1 Prepared under Contract No. NAS 1-3800 by THE BOEING COMPANY Seattle, Wash. for Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sole by the Clearinghouse for Federal Scientific and Technical Information Springfield, Virginia 22151 - CFSTI price $3.00 CONTENTS Page No. 1.0 LUNAR ORBITER II MISSION SUMMARY 1 1.1 INTRODUCTION 4 1.1.1 Program Description 4 1.1.2 Program Management 5 1.1.3 Program Objectives 6 1.1.3.1 Mission II Objectives 6 1.1.4 Mission Design 8 1.1.5 Flight Vehicle Description 12 1.2 LAUNCH PREPARATION AND OPERATIONS 19 1.2.1 Launch Vehicle Preparation 19 1.2.2 Spacecraft Preparation 21 1.2.3 Launch Countdown 21 1.2.4 Launch Phase 22 1.2.4.1 Flight Vehicle Performance 22 1.2.5 Data Acquisition 24 1.3 MISSION OPERATIONS 29 1.3.1 Mission Profile 29 1.3.2 Spacecraft Performance 31 1.3.2.1 Photo Subsystem Performance 32 1.3.2.2 Power Subsystem Performance 34 1.3.2.3 Communications -
Space Isotopic Power Systems
Space isotopiC power systems With the technology sound and growing, and units already built for missions ranging from 120 days to 5 years, the designer can and should plan appropriate space application of isotopic systems BY CAPT. R. T. CARPENTER, USAF U.S. Atomic Energy Commission A new space power system technology technology, and aerospace nuclear Concurrently, the terrestrial appli -isotopic power-has developed to safety technology contributed by the cations-the Snap-7 programs-sus the point where it can and should be program and used as a foundation for tained the isotopic power development considered by the space-vehicle de follow-on space isotopic power-system program and promoted the fission signer for use in many types of mis developments. product separations and processing sions. Because of this sound technical capability that exists within the Com The' Atomic Energy Commission's basis, the Commission's space-oriented mission today! The interest among isotopic space power program dates isotopic power development program terrestrial power users-the Navy, back to several years before Sputnik has made a steady, although some Weather Bureau, and Coast Guard I, but the program suffered a severe times slow, comeback through a series was sufficiently strong to sup:port this setback in 1959 when the Snap-1A of events since 1959, so that today a . fuels production program, whe:r:eas the generator development program was program technically comparable to interest in Snap-1A had been inade cancelled.' This pioneer program was Snap-1A could once more be under quate. At the same time, significant not completed because it may have taken with a high probability of suc quantities of the long-lived alpha been tt;lO ambitious for its day. -
Martian Ice How One Neutrino Changed Astrophysics Remembering Two Former League Presidents
Published by the Astronomical League Vol. 71, No. 3 June 2019 MARTIAN ICE HOW ONE NEUTRINO 7.20.69 CHANGED ASTROPHYSICS 5YEARS REMEMBERING TWO APOLLO 11 FORMER LEAGUE PRESIDENTS ONOMY T STR O T A H G E N P I E G O Contents N P I L R E B 4 . President’s Corner ASTRONOMY DAY Join a Tour This Year! 4 . All Things Astronomical 6 . Full Steam Ahead OCTOBER 5, From 37,000 feet above the Pacific Total Eclipse Flight: Chile 7 . Night Sky Network 2019 Ocean, you’ll be high above any clouds, July 2, 2019 For a FREE 76-page Astronomy seeing up to 3¼ minutes of totality in a PAGE 4 9 . Wanderers in the Neighborhood dark sky that makes the Sun’s corona look Day Handbook full of ideas and incredibly dramatic. Our flight will de- 10 . Deep Sky Objects suggestions, go to: part from and return to Santiago, Chile. skyandtelescope.com/2019eclipseflight www.astroleague.org Click 12 . International Dark-Sky Association on "Astronomy Day” Scroll 14 . Fire & Ice: How One Neutrino down to "Free Astronomy Day African Stargazing Safari Join astronomer Stephen James ̃̃̃Changed a Field Handbook" O’Meara in wildlife-rich Botswana July 29–August 4, 2019 for evening stargazing and daytime PAGE 14 18 . Remembering Two Former For more information, contact: safari drives at three luxury field ̃̃̃Astronomical League Presidents Gary Tomlinson camps. Only 16 spaces available! Astronomy Day Coordinator Optional extension to Victoria Falls. 21 . Coming Events [email protected] skyandtelescope.com/botswana2019 22 . Gallery—Moon Shots 25 . Observing Awards Iceland Aurorae September 26–October 2, 2019 26 . -
Indication, from Pioneer 10/11, Galileo and Ulysses Data, of an Apparent Anomalous, Weak, Long-Range Acceleration”
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by CERN Document Server Comment on \Indication, from Pioneer 10/11, Galileo and Ulysses Data, of an Apparent Anomalous, Weak, Long-Range Acceleration" J. I. Katz Department of Physics and McDonnell Center for the Space Sciences Washington U., St. Louis, Mo. 63130 [email protected] (December 4, 1998) Pacs numbers: 04.80.-y, 95.10.Eg, 95.55.Pe Typeset using REVTEX 1 This paper [1] may have underestimated the acceleration resulting from the radiation of waste heat by the Pioneer spacecraft RTG. These generators are not very efficient; theoretical efficiencies may be as high as 20% [2] but RTG used in spacecraft more typically have electrical efficiencies of about 6% when new [3], which decline slowly as the thermoelectric material degrades and radioactive decay reduces the Carnot efficiency. Specific parameters and detailed design information for Pioneer are difficult to obtain so I adopt an initial electrical efficiency of 6%. Then the electric power at launch of 160 W [1] implied a thermal power of 2.67 kW and a waste heat of 2.51 kW. In 1997 the thermal power, decaying with thehalflifeofPu238 of 87.74 y, was 2.19 kW and the electrical power of 80 W [1] implied a waste heat of 2.11 kW. The power of a collimated beam sufficient to explain the reported anomalous acceleration aP is 85 W [1]. The same force can be obtained from the present rejected waste heat if it is radiated with cos θ =0:040, where θ is the angle between the direction of radiation and a ray from the Sun.h Ifi the 72 W of dissipated electrical power (allowing for 8 W radiated by the antenna) are radiated from the back of the spacecraft according to Lambert’s law the RTG waste heat need only give the thrust of a 37 W collimated beam, requiring cos θ =0:018. -
Project Apollo: Americans to the Moon 440 Document II-1 Document Title
440 Project Apollo: Americans to the Moon Document II-1 Document Title: NASA, “ Minutes of Meeting of Research Steering Committee on Manned Space Flight,” 25–26 May 1959. Source: Folder 18675, NASA Historical Reference Collection, History Division, NASA Headquarters, Washington, DC. Within less than a year after its creation, NASA began looking at follow-on programs to Project Mercury, the initial human spacefl ight effort. A Research Steering Committee on Manned Space Flight was created in spring 1959; it consisted of top-level representatives of all of the NASA fi eld centers and NASA Headquarters. Harry J. Goett from Ames, but soon to be head of the newly created Goddard Space Flight Center, was named chair of the committee. The fi rst meeting of the committee took place on 25 and 26 May 1959, in Washington. Those in attendance provided an overview of research and thinking related to human spacefl ight at various NASA centers, the Jet Propulsion Laboratory (JPL), and the High Speed Flight Station (HSFS) at Edwards Air Force Base. George Low, then in charge of human spacefl ight at NASA Headquarters, argued for making a lunar landing NASA’s long-term goal. He was backed up by engineer and designer Maxime Faget of the Space Task Group of the Langley Research Center and Bruce Lundin of the Lewis Research Center. After further discussion at its June meeting, the Committee agreed on the lunar landing objective, and by the end of the year a lunar landing was incorporated into NASA’s 10-year plan as the long-range objective of the agency’s human spacefl ight program. -
NASA and Planetary Exploration
**EU5 Chap 2(263-300) 2/20/03 1:16 PM Page 263 Chapter Two NASA and Planetary Exploration by Amy Paige Snyder Prelude to NASA’s Planetary Exploration Program Four and a half billion years ago, a rotating cloud of gaseous and dusty material on the fringes of the Milky Way galaxy flattened into a disk, forming a star from the inner- most matter. Collisions among dust particles orbiting the newly-formed star, which humans call the Sun, formed kilometer-sized bodies called planetesimals which in turn aggregated to form the present-day planets.1 On the third planet from the Sun, several billions of years of evolution gave rise to a species of living beings equipped with the intel- lectual capacity to speculate about the nature of the heavens above them. Long before the era of interplanetary travel using robotic spacecraft, Greeks observing the night skies with their eyes alone noticed that five objects above failed to move with the other pinpoints of light, and thus named them planets, for “wan- derers.”2 For the next six thousand years, humans living in regions of the Mediterranean and Europe strove to make sense of the physical characteristics of the enigmatic planets.3 Building on the work of the Babylonians, Chaldeans, and Hellenistic Greeks who had developed mathematical methods to predict planetary motion, Claudius Ptolemy of Alexandria put forth a theory in the second century A.D. that the planets moved in small circles, or epicycles, around a larger circle centered on Earth.4 Only partially explaining the planets’ motions, this theory dominated until Nicolaus Copernicus of present-day Poland became dissatisfied with the inadequacies of epicycle theory in the mid-sixteenth century; a more logical explanation of the observed motions, he found, was to consider the Sun the pivot of planetary orbits.5 1.