Iaa Commission Iii Sg 2 – Nuclear Space Power and Propulsion
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A Preliminary Report of the Battle of the Crater, 30 July 1864
Holding the Line A Preliminary Report of The Battle of the Crater 30 July 1864 Adrian Mandzy, Ph. D. Michelle Sivilich, Ph. D. Benjamin Lewis Fitzpatrick, Ph. D. Dan Sivilich Floyd Patrick Davis Kelsey P. Becraft Dakota Leigh Goedel Jeffrey A. McFadden Jessey C. Reed Jaron A. Rucker A PRELIMINARY REPORT ON THE SURVEY OF THE BATTLE OF THE CRATER, 30 JULY 1864 By Adrian Mandzy, Ph.D., Michelle Sivilich, Ph. D., Floyd Patrick Davis, Kelsey P. Becraft, Dakota Leigh Goedel, Jeffrey A. McFadden, Jessey C. Reed, and Jaron A. Rucker With a Contributions by Daniel Sivilich and Dr. Benjamin Lewis Fitzpatrick Report prepared for the Northeast Region Archeology Program National Park Service 115 John Street, 4th Floor Lowell, Massachusetts 01852-1195 _______________________________ Adrian Mandzy Principal Investigator ARPA Permit 2014.PETE.01 2 Abstract In March 2015, faculty and students from Morehead State University’s History program, along with members of the Battlefield Restoration and Archeological Volunteer Organization (BRAVO) conducted a survey of The Crater Battlefield. Fought on 30 July 1864, during the Siege of Petersburg, the Battle of the Crater, according to the National Park Service, is one of the most important events of the Civil War. The participation of African-American troops in the battle and the subsequent execution of black prisoners highlights the racial animosities that were the underpinning causes of this conflict. The goal of this project is to document the level of integrity of any archaeological resources connected with this field of conflict and to examine how far the Union troops advance beyond the mouth of the Crater. -
Mission to Jupiter
This book attempts to convey the creativity, Project A History of the Galileo Jupiter: To Mission The Galileo mission to Jupiter explored leadership, and vision that were necessary for the an exciting new frontier, had a major impact mission’s success. It is a book about dedicated people on planetary science, and provided invaluable and their scientific and engineering achievements. lessons for the design of spacecraft. This The Galileo mission faced many significant problems. mission amassed so many scientific firsts and Some of the most brilliant accomplishments and key discoveries that it can truly be called one of “work-arounds” of the Galileo staff occurred the most impressive feats of exploration of the precisely when these challenges arose. Throughout 20th century. In the words of John Casani, the the mission, engineers and scientists found ways to original project manager of the mission, “Galileo keep the spacecraft operational from a distance of was a way of demonstrating . just what U.S. nearly half a billion miles, enabling one of the most technology was capable of doing.” An engineer impressive voyages of scientific discovery. on the Galileo team expressed more personal * * * * * sentiments when she said, “I had never been a Michael Meltzer is an environmental part of something with such great scope . To scientist who has been writing about science know that the whole world was watching and and technology for nearly 30 years. His books hoping with us that this would work. We were and articles have investigated topics that include doing something for all mankind.” designing solar houses, preventing pollution in When Galileo lifted off from Kennedy electroplating shops, catching salmon with sonar and Space Center on 18 October 1989, it began an radar, and developing a sensor for examining Space interplanetary voyage that took it to Venus, to Michael Meltzer Michael Shuttle engines. -
Copyrighted Material
Index Abulfeda crater chain (Moon), 97 Aphrodite Terra (Venus), 142, 143, 144, 145, 146 Acheron Fossae (Mars), 165 Apohele asteroids, 353–354 Achilles asteroids, 351 Apollinaris Patera (Mars), 168 achondrite meteorites, 360 Apollo asteroids, 346, 353, 354, 361, 371 Acidalia Planitia (Mars), 164 Apollo program, 86, 96, 97, 101, 102, 108–109, 110, 361 Adams, John Couch, 298 Apollo 8, 96 Adonis, 371 Apollo 11, 94, 110 Adrastea, 238, 241 Apollo 12, 96, 110 Aegaeon, 263 Apollo 14, 93, 110 Africa, 63, 73, 143 Apollo 15, 100, 103, 104, 110 Akatsuki spacecraft (see Venus Climate Orbiter) Apollo 16, 59, 96, 102, 103, 110 Akna Montes (Venus), 142 Apollo 17, 95, 99, 100, 102, 103, 110 Alabama, 62 Apollodorus crater (Mercury), 127 Alba Patera (Mars), 167 Apollo Lunar Surface Experiments Package (ALSEP), 110 Aldrin, Edwin (Buzz), 94 Apophis, 354, 355 Alexandria, 69 Appalachian mountains (Earth), 74, 270 Alfvén, Hannes, 35 Aqua, 56 Alfvén waves, 35–36, 43, 49 Arabia Terra (Mars), 177, 191, 200 Algeria, 358 arachnoids (see Venus) ALH 84001, 201, 204–205 Archimedes crater (Moon), 93, 106 Allan Hills, 109, 201 Arctic, 62, 67, 84, 186, 229 Allende meteorite, 359, 360 Arden Corona (Miranda), 291 Allen Telescope Array, 409 Arecibo Observatory, 114, 144, 341, 379, 380, 408, 409 Alpha Regio (Venus), 144, 148, 149 Ares Vallis (Mars), 179, 180, 199 Alphonsus crater (Moon), 99, 102 Argentina, 408 Alps (Moon), 93 Argyre Basin (Mars), 161, 162, 163, 166, 186 Amalthea, 236–237, 238, 239, 241 Ariadaeus Rille (Moon), 100, 102 Amazonis Planitia (Mars), 161 COPYRIGHTED -
Nasa Tm X-1864 *
NASA TECHNICAL. • £HP2fKit NASA TM X-1864 * ... MEMORANDUM oo fe *' > ;ff f- •* '• . ;.*• f PROPULSION • FOR *MANN1D E30PLORATION-k '* *Of THE SOEAE " • » £ Moedkel • - " *' ' ' y Lem$ Research Center Cleveland, Qbt® NATIONAL AERONAUTICS AND SFACE ADMINISTRATION • WASHINGTON, D. €, * AUCUST 1969 NASA TM X-1864 PROPULSION SYSTEMS FOR MANNED EXPLORATION OF THE SOLAR SYSTEM By W. E. Moeckel Lewis Research Center Cleveland, Ohio NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and. Technical Information Springfield, Virginia 22151 - CFSTI price $3.00 ABSTRACT What propulsion systems are in sight for fast interplanetary travel? Only a few show promise of reducing trip times to values comparable to those of 16th century terrestrial expeditions. The first portion of this report relates planetary round-trip times to the performance parameters of two types of propulsion systems: type I is specific-impulse limited (with high thrust), and type n is specific-mass limited (with low thrust). The second part of the report discusses advanced propulsion concepts of both types and evaluates their limitations. The discussion includes nuclear-fission . rockets (solid, liquid, and gaseous core), nuclear-pulse propulsion, nuclear-electric rockets, and thermonuclear-fusion rockets. Particular attention is given to the last of these, because it is less familiar than the others. A general conclusion is that the more advanced systems, if they prove feasible, will reduce trip time to the near planets by factors of 3 to 5, and will make several outer planets accessible to manned exploration. PROPULSION SYSTEMS FOR MANNED EXPLORATION OF THE SOLAR SYSTEM* byW. E. Moeckel Lewis Research Center SUMMARY What propulsion systems are in sight for fast interplanetary travel? Only a few show promise of reducing trip times to values comparable to those of 16th century terrestrial expeditions. -
No. 40. the System of Lunar Craters, Quadrant Ii Alice P
NO. 40. THE SYSTEM OF LUNAR CRATERS, QUADRANT II by D. W. G. ARTHUR, ALICE P. AGNIERAY, RUTH A. HORVATH ,tl l C.A. WOOD AND C. R. CHAPMAN \_9 (_ /_) March 14, 1964 ABSTRACT The designation, diameter, position, central-peak information, and state of completeness arc listed for each discernible crater in the second lunar quadrant with a diameter exceeding 3.5 km. The catalog contains more than 2,000 items and is illustrated by a map in 11 sections. his Communication is the second part of The However, since we also have suppressed many Greek System of Lunar Craters, which is a catalog in letters used by these authorities, there was need for four parts of all craters recognizable with reasonable some care in the incorporation of new letters to certainty on photographs and having diameters avoid confusion. Accordingly, the Greek letters greater than 3.5 kilometers. Thus it is a continua- added by us are always different from those that tion of Comm. LPL No. 30 of September 1963. The have been suppressed. Observers who wish may use format is the same except for some minor changes the omitted symbols of Blagg and Miiller without to improve clarity and legibility. The information in fear of ambiguity. the text of Comm. LPL No. 30 therefore applies to The photographic coverage of the second quad- this Communication also. rant is by no means uniform in quality, and certain Some of the minor changes mentioned above phases are not well represented. Thus for small cra- have been introduced because of the particular ters in certain longitudes there are no good determi- nature of the second lunar quadrant, most of which nations of the diameters, and our values are little is covered by the dark areas Mare Imbrium and better than rough estimates. -
Pulsed Fusion Space Propulsion: Computational Ideal Magneto-Hydro Dynamics of a Magnetic Flux Compression Reaction Chamber
Pulsed Fusion Space Propulsion: Computational Ideal Magneto-Hydro Dynamics of a Magnetic Flux Compression Reaction Chamber G. Romanelli Master of Science Thesis Space Systems Engineering PULSED FUSION SPACE PROPULSION: COMPUTATIONAL IDEAL MAGNETO-HYDRO DYNAMICS OFA MAGNETIC FLUX COMPRESSION REACTION CHAMBER by Gherardo ROMANELLI to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Friday February 26, 2016 at 10:00 AM. Student number: 4299876 Thesis committee: Dr. A. Cervone, TU Delft, supervisor Prof. Dr. E. K. A. Gill, TU Delft Dr. Ir. E. Mooij, TU Delft Prof. A. Mignone, Politecnico di Torino An electronic version of this thesis is available at http://repository.tudelft.nl/. To boldly go where no one has gone before. James T. Kirk ACKNOWLEDGEMENTS First of all I would like to thank my supervisor Dr. A. Cervone who has always sup- ported me despite my “quite exotic” interests. He left me completely autonomous in shaping my thesis project, and still, was always there every time I needed help. Then, I would of course like to thank Prof. A. Mignone who decided to give his contribute to this seemingly crazy project of mine. His advice arrived just in time to give an happy ending to this story. Il ringraziamento più grande, però, va di certo alla mia famiglia. Alla mia mamma e a mio babbo, perché hanno sempre avuto fiducia in me e non hanno mai chiesto ragioni o spiegazioni alle mie scelte. Ai miei nonni, perché se di punto in bianco, un giorno di novembre ho deciso di intraprendere questa lunga strada verso l’Olanda, l’ho potuto fare anche per merito loro. -
Liquid Argon
Safetygram 8 Liquid argon Liquid argon is tasteless, colorless, odorless, noncorrosive, nonflammable, and extremely cold. Belonging to the family of rare gases, argon is the most plentiful, making up approximately 1% of the earth’s atmosphere. It is monatomic and extremely inert, forming no known chemical compounds. Since argon is inert, special materials of construction are not required. However, materials of construction must be selected to withstand the low temperature of liquid argon. Vessels and piping should be designed to American Society of Mechanical Engineers (ASME) specifications or the Department of Transportation (DOT) codes for the pressures and temperatures involved. Although used more commonly in the gaseous state, argon is commonly stored and transported as a liquid, affording a more cost-effective way of providing product supply. Liquid argon is a cryogenic liquid. Cryogenic liquids are liquefied gases that have a normal boiling point below –130°F (–90°C). Liquid argon has a boiling point of –303°F (–186°C). The temperature difference between the product and the surrounding environment, even in winter, is substantial. Keeping this surrounding heat from the product requires special equipment to store and handle cryogenic liquids. A typical system consists of the following components: a cryogenic storage tank, one or more vaporizers, a pressure control system, and all of the piping required for fill, vaporization. The cryogenic tank is constructed, in principle, like a vacuum bottle. It is designed to keep heat away from the liquid that is contained in the inner vessel. Vaporizers convert the liquid argon to its gaseous state. A pressure control manifold controls the pressure at which the gas is fed to the process. -
2021 Transpacific Yacht Race Event Program
TRANSPACTHE FIFTY-FIRST RACE FROM LOS ANGELES 2021 TO HONOLULU 2 0 21 JULY 13-30, 2021 Comanche: © Sharon Green / Ultimate Sailing COMANCHE Taxi Dancer: © Ronnie Simpson / Ultimate Sailing • Hamachi: © Team Hamachi HAMACHI 2019 FIRST TO FINISH Official race guide - $5.00 2019 OVERALL CORRECTED TIME WINNER P: 808.845.6465 [email protected] F: 808.841.6610 OFFICIAL HANDBOOK OF THE 51ST TRANSPACIFIC YACHT RACE The Transpac 2021 Official Race Handbook is published for the Honolulu Committee of the Transpacific Yacht Club by Roth Communications, 2040 Alewa Drive, Honolulu, HI 96817 USA (808) 595-4124 [email protected] Publisher .............................................Michael J. Roth Roth Communications Editor .............................................. Ray Pendleton, Kim Ickler Contributing Writers .................... Dobbs Davis, Stan Honey, Ray Pendleton Contributing Photographers ...... Sharon Green/ultimatesailingcom, Ronnie Simpson/ultimatesailing.com, Todd Rasmussen, Betsy Crowfoot Senescu/ultimatesailing.com, Walter Cooper/ ultimatesailing.com, Lauren Easley - Leialoha Creative, Joyce Riley, Geri Conser, Emma Deardorff, Rachel Rosales, Phil Uhl, David Livingston, Pam Davis, Brian Farr Designer ........................................ Leslie Johnson Design On the Cover: CONTENTS Taxi Dancer R/P 70 Yabsley/Compton 2019 1st Div. 2 Sleds ET: 8:06:43:22 CT: 08:23:09:26 Schedule of Events . 3 Photo: Ronnie Simpson / ultimatesailing.com Welcome from the Governor of Hawaii . 8 Inset left: Welcome from the Mayor of Honolulu . 9 Comanche Verdier/VPLP 100 Jim Cooney & Samantha Grant Welcome from the Mayor of Long Beach . 9 2019 Barndoor Winner - First to Finish Overall: ET: 5:11:14:05 Welcome from the Transpacific Yacht Club Commodore . 10 Photo: Sharon Green / ultimatesailingcom Welcome from the Honolulu Committee Chair . 10 Inset right: Welcome from the Sponsoring Yacht Clubs . -
Safety Consideration on Liquid Hydrogen
Safety Considerations on Liquid Hydrogen Karl Verfondern Helmholtz-Gemeinschaft der 5/JULICH Mitglied FORSCHUNGSZENTRUM TABLE OF CONTENTS 1. INTRODUCTION....................................................................................................................................1 2. PROPERTIES OF LIQUID HYDROGEN..........................................................................................3 2.1. Physical and Chemical Characteristics..............................................................................................3 2.1.1. Physical Properties ......................................................................................................................3 2.1.2. Chemical Properties ....................................................................................................................7 2.2. Influence of Cryogenic Hydrogen on Materials..............................................................................9 2.3. Physiological Problems in Connection with Liquid Hydrogen ....................................................10 3. PRODUCTION OF LIQUID HYDROGEN AND SLUSH HYDROGEN................................... 13 3.1. Liquid Hydrogen Production Methods ............................................................................................ 13 3.1.1. Energy Requirement .................................................................................................................. 13 3.1.2. Linde Hampson Process ............................................................................................................15 -
MULTIPHYSICS DESIGN and SIMULATION of a TUNGSTEN-CERMET NUCLEAR THERMAL ROCKET a Thesis by BRAD APPEL Submitted to the Office O
MULTIPHYSICS DESIGN AND SIMULATION OF A TUNGSTEN-CERMET NUCLEAR THERMAL ROCKET A Thesis by BRAD APPEL Submitted to the Office of Graduate Studies of Texas A&M University in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE August 2012 Major Subject: Nuclear Engineering Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket Copyright 2012 Brad Appel ii MULTIPHYSICS DESIGN AND SIMULATION OF A TUNGSTEN-CERMET NUCLEAR THERMAL ROCKET A Thesis by BRAD APPEL Submitted to the Office of Graduate Studies of Texas A&M University in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Approved by: Chair of Committee, Karen Vierow Committee Members, Shannon Bragg-Sitton Paul Cizmas Head of Department, Yassin Hassan August 2012 Major Subject: Nuclear Engineering iii iii ABSTRACT Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. (August 2012) Brad Appel, B.S., Purdue University Chair of Advisory Committee: Dr. Karen Vierow The goal of this research is to apply modern methods of analysis to the design of a tungsten-cermet Nuclear Thermal Rocket (NTR) core. An NTR is one of the most viable propulsion options for enabling piloted deep-space exploration. Concerns over fuel safety have sparked interest in an NTR core based on tungsten-cermet fuel. This work investigates the capability of modern CFD and neutronics codes to design a cermet NTR, and makes specific recommendations for the configuration of channels in the core. First, the best CFD practices available from the commercial package Star-CCM+ are determined by comparing different modeling options with a hot-hydrogen flow experiment. -
NETS 2020 Template
بÀƵƧǘȁǞƧƊǶ §ȲȌǐȲƊǿ ƊƧDzɈȌɈǘƵwȌȌȁƊȁƮȌȁ ɈȌwƊȲȺɈǘȲȌɐǐǘƊƮɨƊȁƧǞȁǐ خȁɐƧǶƵƊȲɈƵƧǘȁȌǶȌǐǞƵȺƊȁƮ ǞȁȁȌɨƊɈǞȌȁ ǞȺ ȺȯȌȁȺȌȲƵƮ Ʀɯ ɈǘƵ ƊDz ªǞƮǐƵ yƊɈǞȌȁƊǶ ׁׂ׀ׂ y0À² ÀǘǞȺ ƧȌȁǏƵȲƵȁƧƵ خׁׂ׀ׂ ةɈǘ׀׃ƊȁƮ ɩǞǶǶƦƵ ǘƵǶƮ ǏȲȌǿȯȲǞǶ ׂ׆ɈǘٌةmƊƦȌȲƊɈȌȲɯ ɩǞǶǶ ƦƵ ǘƵǶƮ ɨǞȲɈɐƊǶǶɯ ȺȌ ɈǘƊɈ ɈǘƵ ƵȁɈǞȲƵ y0À² خƧȌǿǿɐȁǞɈɯǿƊɯȯƊȲɈǞƧǞȯƊɈƵǞȁɈǘǞȺƵɮƧǞɈǞȁǐǿƵƵɈǞȁǐ ǐȌɨخȌȲȁǶخخׁׂ׀ȁƵɈȺׂششبǘɈɈȯȺ Nuclear and Emerging Technologies for Space Sponsored by Oak Ridge National Laboratory, April 26th-30th, 2021. Available online at https://nets2021.ornl.gov Table of Contents Table of Contents .................................................................................................................................................... 1 Thanks to the NETS2021 Sponsors! ...................................................................................................................... 2 Nuclear and Emerging Technologies for Space 2021 – Schedule at a Glance ................................................. 3 Nuclear and Emerging Technologies for Space 2021 – Technical Sessions and Panels By Track ............... 6 Nuclear and Emerging Technologies for Space 2021 – Lightning Talk Final Program ................................... 8 Nuclear and Emerging Technologies for Space 2021 – Track 1 Final Program ............................................. 11 Nuclear and Emerging Technologies for Space 2021 – Track 2 Final Program ............................................. 14 Nuclear and Emerging Technologies for Space 2021 – Track 3 Final Program ............................................. 18 -
Thales Alenia Space Experience on Plasma Propulsion
Thales Alenia Space Experience on Plasma Propulsion IEPC-2007-301 Presented at the 30th International Electric Propulsion Conference, Florence, Italy September 17-20, 2007 Michel LYSZYK* and Laurent LECARDONNEL.† Thales Alenia Space, Cannes, 06150, France Abstract: Thales Alenia Space experience on plasma propulsion has been developed in the frame of Stentor, Astra 1K and GEI programs with plasma propulsion systems using SPT100 thrusters manufactured by Fakel and commercialized by Snecma . The PPS (plasma propulsion system) use in house equipments such as Power Processing Unit (PPU) manufactured by TAS-ETCA in Charleroi and the Thruster Orientation Mechanism (TOM) manufactured by TAS-France in Cannes . The PPS subsystem is used on board our SpaceBus satellite family to perform North-South station keeping. The on going activity on the XPS (Xenon Propulsion System) is devoted to the next European platform Alphabus currently under joint development by Thales Alenia Space and Astrium with CNES and ESA support. The XPS uses also the PPU manufactured by TAS-ETCA , the TOM manufactured by TAS-France and the Xe tank developed by TAS-Italy ; it use also the PPS1350 thruster under qualification by Snecma , a xenon regulator and a latch valve under development at Marotta Ireland. I. Introduction HIS document describes the Thales Alenia Space experience gained through Stentor , Astra 1K , GEI, T Spacebus and Alphabus programs on plasma Hall effect thrusters propulsion subsystems . For Spacebus application a description of the subsystem is given together with the general achieved performances . For Alphabus application a general status of the on going activities is given . * Head of electric propulsion section, Propulsion Department, [email protected].