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Quantitative Composition and Granulometry of Aeolian Bedforms in Endeavour and Gale Craters Inferred from Visible Near-Infrared Spectra
45th Lunar and Planetary Science Conference (2014) 1431.pdf QUANTITATIVE COMPOSITION AND GRANULOMETRY OF AEOLIAN BEDFORMS IN ENDEAVOUR AND GALE CRATERS INFERRED FROM VISIBLE NEAR-INFRARED SPECTRA. Mathieu G.A. Lapotre1, Bethany L. Ehlmann1,2, Raymond E. Arvidson3. 1Division of Geological and Planetary Sciences, California Institute of Technology, Pasadena, CA, USA. 2Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA, USA, 3Department of Earth & Planetary Sciences, Washington University in St. Louis, MO, USA. Introduction: Modern Mars is a wind world. Its ing Spectrometer for Mars (CRISM) visible near- surface hosts a variety of aeolian features, such as line- infrared spectra (VISIR). The goal of this study is to ar, barchan and star dunes, ripples, granule ripples, compare inversions made from orbit to ground truth yardangs and ventifacts [1]. Even though active sand provided by instruments aboard Opportunity at En- transport was observed at the surface [2], it is not clear deavour Crater, Terra Meridiani and Curiosity in Gale whether all of the preserved aeolian bedforms are ac- crater. tive. In particular, transverse aeolian ridges have been We use Hapke’s bidirectional reflectance spectros- suggested to be remnant dunes that formed under past copy theory [6] to invert for optical constants of miner- climatic conditions [3]. als from laboratory spectra [e.g., 7, 8]. These are used Sand transport is largely controlled by the size and to compute single scattering albedos of mineral the density of the grains [4]. Moreover, dunes and rip- endmember components of varying grain sizes. We use ples form in unimodally distributed sand particles from an atmospheric radiative transfer approach, DISORT different instabilities, and the wavelengths of these [9], to correct the CRISM spectra for the effects of the different bedforms do not have the same dependence Martian atmosphere. -
L AUNCH SYSTEMS Databk7 Collected.Book Page 18 Monday, September 14, 2009 2:53 PM Databk7 Collected.Book Page 19 Monday, September 14, 2009 2:53 PM
databk7_collected.book Page 17 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS databk7_collected.book Page 18 Monday, September 14, 2009 2:53 PM databk7_collected.book Page 19 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS Introduction Launch systems provide access to space, necessary for the majority of NASA’s activities. During the decade from 1989–1998, NASA used two types of launch systems, one consisting of several families of expendable launch vehicles (ELV) and the second consisting of the world’s only partially reusable launch system—the Space Shuttle. A significant challenge NASA faced during the decade was the development of technologies needed to design and implement a new reusable launch system that would prove less expensive than the Shuttle. Although some attempts seemed promising, none succeeded. This chapter addresses most subjects relating to access to space and space transportation. It discusses and describes ELVs, the Space Shuttle in its launch vehicle function, and NASA’s attempts to develop new launch systems. Tables relating to each launch vehicle’s characteristics are included. The other functions of the Space Shuttle—as a scientific laboratory, staging area for repair missions, and a prime element of the Space Station program—are discussed in the next chapter, Human Spaceflight. This chapter also provides a brief review of launch systems in the past decade, an overview of policy relating to launch systems, a summary of the management of NASA’s launch systems programs, and tables of funding data. The Last Decade Reviewed (1979–1988) From 1979 through 1988, NASA used families of ELVs that had seen service during the previous decade. -
Acidic Fluids Across Mars: Detections of Magnesium-Nickel Sulfates
ACIDIC FLUIDS ACROSS MARS: DETECTIONS OF MAGNESIUM-NICKEL SULFATES. A. S. Yen1, D. W. Ming2, R. Gellert3, D. W. Mittlefehldt2, E. B. Rampe4, D. T. Vaniman5, L. M. Thompson6, R. V. Morris2, B. C. Clark7, S. J. VanBommel3, R. E. Arvidson8, 1JPL- Caltech ([email protected]), 2NASA-JSC, 3University of Guelph, 4Aerodyne Industries, 5Planetary Science Institute, 6University of New Brunswick, 7Space Science Insti- tute, 7Washington University in St. Louis. Introduction: Calcium, magnesium and ferric iron sulfates have been detected by the instrument suites on the Mars rovers. A subset of the magnesium sulfates show clear associations with nickel. These associations indicate Ni2+ co-precipitation with or substitution for Mg2+ from sulfate-saturated solutions. Nickel is ex- tracted from primary rocks almost exclusively at pH values less than 6, constraining the formation of these Mg-Ni sulfates to mildly to strongly acidic conditions. There is clear evidence for aqueous alteration at the rim of Endeavour Crater (Meridiani Planum), in the Murray formation mudstone (Gale Crater), and near Home Plate (Gusev Crater). The discovery of Mg-Ni sulfates at these locations indicates a history of fluid- rock interactions at low pH. Fig 1: Histogram showing significant concentrations Mars Rovers: The Mars Exploration Rovers of sulfur in APXS analyses by the three Mars rovers (MER), Spirit and Opportunity, landed in January 2004 (mean value: 6.6%). at Gusev Crater and Meridiani Planum, respectively. Spirit traversed over 7.7 km through 2210 sols of sur- face operations, and Opportunity is currently on the degraded rim of Endeavour Crater after 4600 sols and 44 km of traverse. -
PCEC V2.3 (For Real This Time)
PCEC v2.3 (For Real This Time) 2021 NASA Cost & Schedule Symposium 14 Apr 2021 Brian Alford Mark Jacobs Booz Allen Hamilton TGS Consultants Shawn Hayes Richard Webb TGS Consultants KAR Enterprises NASA MSFC Victory MIPSSSolutions Team SB Diversity Outline • PCEC Overview • Robotic SC Updates • CASTS Updates • PCEC v2.3 Interface Updates • Closing Victory Solutions MIPSS Team 2 What is PCEC? • The Project Cost Estimating Capability (PCEC) is the primary NASA in-house developed parametric tool for estimating the cost of robotic missions, launch vehicles, crewed vehicles, etc. – Overarching tool for creating an estimate that spans the full NASA WBS – CERs included out-of-the-box for estimating the costs of a flight system (e.g., thermal) and support functions (e.g., project management) – Connects to other NASA-sponsored specialized tools to cover the complete NASA WBS (e.g., NICM, MOCET) – Excel-based (presented as add-in in the Ribbon) with completely visible calculations and code – Consists of the PCEC Interface (the Ribbon and supporting code) and the PCEC Library (the artifacts used to estimate cost) – Available to the General Public Victory Solutions MIPSS Team 3 What is PCEC? Cont’d • PCEC comprises two primary ‘models’, offered seamlessly to the user under a single, integrated tool – Robotic Spacecraft (Robotic SC) – Crewed and Space Transportation Systems (CASTS) • These models have separate data normalizations, collections of CERs, core WBSs, modeling approaches, estimating template worksheets, and scope – Estimating artifacts constitute -
+ 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 -
Mars Reconnaissance Orbiter and Opportunity Observations Of
PUBLICATIONS Journal of Geophysical Research: Planets RESEARCH ARTICLE Mars Reconnaissance Orbiter and Opportunity 10.1002/2014JE004686 observations of the Burns formation: Crater Key Point: hopping at Meridiani Planum • Hydrated Mg and Ca sulfate Burns formation minerals mapped with MRO R. E. Arvidson1, J. F. Bell III2, J. G. Catalano1, B. C. Clark3, V. K. Fox1, R. Gellert4, J. P. Grotzinger5, and MER data E. A. Guinness1, K. E. Herkenhoff6, A. H. Knoll7, M. G. A. Lapotre5, S. M. McLennan8, D. W. Ming9, R. V. Morris9, S. L. Murchie10, K. E. Powell1, M. D. Smith11, S. W. Squyres12, M. J. Wolff3, and J. J. Wray13 1 2 Correspondence to: Department of Earth and Planetary Sciences, Washington University in Saint Louis, Missouri, USA, School of Earth and Space R. E. Arvidson, Exploration, Arizona State University, Tempe, Arizona, USA, 3Space Science Institute, Boulder, Colorado, USA, 4Department of [email protected] Physics, University of Guelph, Guelph, Ontario, Canada, 5Division of Geological and Planetary Sciences, California Institute of Technology, Pasadena, California, USA, 6U.S. Geological Survey, Astrogeology Science Center, Flagstaff, Arizona, USA, 7 8 Citation: Department of Organismic and Evolutionary Biology, Harvard University, Cambridge, Massachusetts, USA, Department Arvidson, R. E., et al. (2015), Mars of Geosciences, Stony Brook University, Stony Brook, New York, USA, 9NASA Johnson Space Center, Houston, Texas, USA, Reconnaissance Orbiter and Opportunity 10Applied Physics Laboratory, Johns Hopkins University, Laurel, Maryland, USA, 11NASA Goddard Space Flight Center, observations of the Burns formation: Greenbelt, Maryland, USA, 12Department of Astronomy, Cornell University, Ithaca, New York, USA, 13School of Earth and Crater hopping at Meridiani Planum, J. -
The Degradational History of Endeavour Crater, Mars. J. A
The Degradational History of Endeavour Crater, Mars. J. A. Grant1, T. J. Parker2, L. S. Crumpler3, S. A. Wilson1, M. P. Golombek2, and D. W. Mittlefehldt4, Smithsonian Institution, NASM CEPS, 6th at Independence SW, Washington, DC, 20560 ([email protected]), 2Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Drive, Pasadena, CA 91109, 3New Mexico Museum of Natural History & Science, 1801 Mountain Rd NW, Albuquerque, NM, 87104, 4Astromaterials Research Office, NASA Johnson Space Center, 2101 NASA Parkway, Houston, TX 77058. Endeavour crater (2.28°S, 354.77°E) is a Noachian-aged 22 km-diameter impact structure of complex morphology in Meridiani Planum. The degradation state of the crater has been studied using Mars Reconnaissance Orbiter and Opportunity rover data. Exposed rim segments rise ~10 m to ~100 m above the level of the embaying Burns Formation and the crater is 200-500 m deep with the southern interior wall exposing over ~300 m relief. Both pre-impact rocks (Matijevic Formation) and Endeavour impact ejecta (Shoemaker Formation) are present at Cape York, but only the Shoemaker crops out (up to ~140 m) along the rim segment from Murray Ridge to Cape Tribulation. Study of pristine complex craters Bopolu and Tooting, and morphometry of other martian complex craters, enables us to approximate Endeavour’s pristine form. The original rim likely averaged 410 m ±200 m in elevation and a 250-275 m section of ejecta (±50-60 m) would have composed a significant fraction of the rim height. The original crater depth was likely between 1.5 km and 2.2 km. -
Mars Exploration - a Story Fifty Years Long Giuseppe Pezzella and Antonio Viviani
Chapter Introductory Chapter: Mars Exploration - A Story Fifty Years Long Giuseppe Pezzella and Antonio Viviani 1. Introduction Mars has been a goal of exploration programs of the most important space agencies all over the world for decades. It is, in fact, the most investigated celestial body of the Solar System. Mars robotic exploration began in the 1960s of the twentieth century by means of several space probes sent by the United States (US) and the Soviet Union (USSR). In the recent past, also European, Japanese, and Indian spacecrafts reached Mars; while other countries, such as China and the United Arab Emirates, aim to send spacecraft toward the red planet in the next future. 1.1 Exploration aims The high number of mission explorations to Mars clearly points out the impor- tance of Mars within the Solar System. Thus, the question is: “Why this great interest in Mars exploration?” The interest in Mars is due to several practical, scientific, and strategic reasons. In the practical sense, Mars is the most accessible planet in the Solar System [1]. It is the second closest planet to Earth, besides Venus, averaging about 360 million kilometers apart between the furthest and closest points in its orbit. Earth and Mars feature great similarities. For instance, both planets rotate on an axis with quite the same rotation velocity and tilt angle. The length of a day on Earth is 24 h, while slightly longer on Mars at 24 h and 37 min. The tilt of Earth axis is 23.5 deg, and Mars tilts slightly more at 25.2 deg [2]. -
INTRODUCTION to SPACE EXPLORATION Creating a Time Capsule
INTRODUCTION TO SPACE EXPLORATION Creating a Time Capsule Grade Level: 5 - 8 Suggested TEKS Language Arts - 5.15 6.15 7.15 8.15 Social Studies - 5.18 6.20 7.20 8.20 Time Required: 30 - 45 minutes Art - 5.2 6.2 7.2 8.2 Computer - 5.2 6.2 7.2 8.2 Suggested SCANS Countdown: Writing paper Interpersonal. Interprets and Communicates Information National Science and Math Standards Pencils Science as Inquiry, Physical Science, Earth & Space Science, Science & Technology, History & Nature of Science, Measurement, Observing, Communicating Ignition: For decades, space colonies have been the creation of science fiction writers. However, with world population growing at an alarming rate, the concept of a second home in space could very likely become a stark reality. Already, a number of visionary scientists have drawn up plans for off-earth habitats. Biosphere II near Tucson, Arizona is an example. Additionally, NASA has future plans for a mission to Mars in the next 20 years. It certainly appears that earth will not always be our home. With this in mind, ask the students to consider the scenario suggested next in "Liftoff." Liftoff: You will have the opportunity to bury a time capsule, a sealed and durable box, which will be opened after one hundred years. Future discoverers of the box will be able to guess from the contents what your life was like 100 years before their time. Below are six different categories. For each category, choose an object that would best represent it. Keep in mind that you may choose items like photographs, scrapbooks, films or videos, books, newspapers, miniature models, and other favorite mementos. -
Los Motores Aeroespaciales, A-Z
Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 1/12 Página: 1 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 Los Motores Aeroespaciales, A-Z (The Aerospace En- gines, A-Z) Versión 12 2018 por Ricardo Miguel Vidal * * * -MOTOR: Máquina que transforma en movimiento la energía que recibe. (sea química, eléctrica, vapor...) Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 1/12 Página: 2 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 Presentación de la edición 2018-V12 (Incluye todas las anteriores versiones y sus Apéndices) La edición 2003 era una publicación en partes que se archiva en Binders por el propio lector (2,3,4 anillas, etc), anchos o estrechos y del color que desease durante el acopio parcial de la edición. Se entregaba por grupos de hojas impresas a una cara (edición 2003), a incluir en los Binders (archivadores). Cada hoja era sustituíble en el futuro si aparecía una nueva misma hoja ampliada o corregida. Este sistema de anillas admitia nuevas páginas con información adicional. Una hoja con adhesivos para portada y lomo identifi caba cada volumen provisional. Las tapas defi nitivas fueron metálicas, y se entregaraban con el 4 º volumen. O con la publicación completa desde el año 2005 en adelante. -Las Publicaciones -parcial y completa- están protegidas legalmente y mediante un sello de tinta especial color VERDE se identifi can los originales. -
10/2/95 Rev EXECUTIVE SUMMARY This Report, Entitled "Hazard
10/2/95 rev EXECUTIVE SUMMARY This report, entitled "Hazard Analysis of Commercial Space Transportation," is devoted to the review and discussion of generic hazards associated with the ground, launch, orbital and re-entry phases of space operations. Since the DOT Office of Commercial Space Transportation (OCST) has been charged with protecting the public health and safety by the Commercial Space Act of 1984 (P.L. 98-575), it must promulgate and enforce appropriate safety criteria and regulatory requirements for licensing the emerging commercial space launch industry. This report was sponsored by OCST to identify and assess prospective safety hazards associated with commercial launch activities, the involved equipment, facilities, personnel, public property, people and environment. The report presents, organizes and evaluates the technical information available in the public domain, pertaining to the nature, severity and control of prospective hazards and public risk exposure levels arising from commercial space launch activities. The US Government space- operational experience and risk control practices established at its National Ranges serve as the basis for this review and analysis. The report consists of three self-contained, but complementary, volumes focusing on Space Transportation: I. Operations; II. Hazards; and III. Risk Analysis. This Executive Summary is attached to all 3 volumes, with the text describing that volume highlighted. Volume I: Space Transportation Operations provides the technical background and terminology, as well as the issues and regulatory context, for understanding commercial space launch activities and the associated hazards. Chapter 1, The Context for a Hazard Analysis of Commercial Space Activities, discusses the purpose, scope and organization of the report in light of current national space policy and the DOT/OCST regulatory mission. -
The Delta Launch Vehicle- Past, Present, and Future
The Space Congress® Proceedings 1981 (18th) The Year of the Shuttle Apr 1st, 8:00 AM The Delta Launch Vehicle- Past, Present, and Future J. K. Ganoung Manager Spacecraft Integration, McDonnell Douglas Astronautics Co. H. Eaton Delta Launch Program, McDonnell Douglas Astronautics Co. Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Ganoung, J. K. and Eaton, H., "The Delta Launch Vehicle- Past, Present, and Future" (1981). The Space Congress® Proceedings. 7. https://commons.erau.edu/space-congress-proceedings/proceedings-1981-18th/session-6/7 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. THE DELTA LAUNCH VEHICLE - PAST, PRESENT AND FUTURE J. K. Ganoung, Manager H. Eaton, Jr., Director Spacecraft Integration Delta Launch Program McDonnell Douglas Astronautics Co. McDonnell Douglas Astronautics Co. INTRODUCTION an "interim space launch vehicle." The THOR was to be modified for use as the first stage, the The Delta launch vehicle is a medium class Vanguard second stage propulsion system, was used expendable booster managed by the NASA Goddard as the Delta second stage and the Vanguard solid Space Flight Center and used by the U.S. rocket motor became Delta's third stage. Government, private industry and foreign coun Following the eighteen month development program tries to launch scientific, meteorological, and failure to launch its first payload into or applications and communications satellites.