N91-28267 Launch Operations Manpower Yesterday, Today
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The Early Explorers by Andrew J
The Early Explorers by Andrew J. LePage August 8, 1999 Among these programs were the next generation of Introduction Explorer satellites the ABMA was planning. In the chaos that swept the United States after the launching of the first Soviet Sputniks, a variety of The First New Explorers satellite programs was sponsored by the Department The first of the new series of larger Explorer satellites of Defense (DoD) to supplement (and in some cases was the 39.7 kilogram (87.5 pound) satellite NASA supplant) the country's flagging "official" satellite designated as S-1. Built by JPL, the spin stabilized program, Vanguard. One of the stronger programs S-1 consisted of a pair of fiberglass cones joined at was sponsored by the ABMA (Army Ballistic Missile their bases with a diameter and height of 76 Agency) with its engineering team lead by the centimeters each. The scientific payload consisted of German rocket expert, Wernher von Braun. Using instruments to study cosmic rays, solar X-ray and the Juno I launch vehicle, the ABMA team launched ultraviolet emissions, micrometeorites, as well as the America's first satellite, Explorer 1, which was built globe's heat balance. This was all powered by a bank by Caltech's Jet Propulsion Laboratory (JPL) (see of 15 nickel-cadmium batteries recharged by 3,000 Explorer: America's First Satellite in the February solar cells mounted on the satellite's exterior. This 1998 issue of SpaceViews). advanced payload was equipped with a timer to turn itself off after a year in orbit. While these first satellites returned a wealth of new data, they were limited by the tiny 11 kilogram (25 Explorer S-1 was launched from Cape Canaveral on pound) payload capability of the Juno I. -
AAS Worldwide Telescope: Seamless, Cross-Platform Data Visualization Engine for Astronomy Research, Education, and Democratizing Data
AAS WorldWide Telescope: Seamless, Cross-Platform Data Visualization Engine for Astronomy Research, Education, and Democratizing Data The Harvard community has made this article openly available. Please share how this access benefits you. Your story matters Citation Rosenfield, Philip, Jonathan Fay, Ronald K Gilchrist, Chenzhou Cui, A. David Weigel, Thomas Robitaille, Oderah Justin Otor, and Alyssa Goodman. 2018. AAS WorldWide Telescope: Seamless, Cross-Platform Data Visualization Engine for Astronomy Research, Education, and Democratizing Data. The Astrophysical Journal: Supplement Series 236, no. 1. Published Version https://iopscience-iop-org.ezp-prod1.hul.harvard.edu/ article/10.3847/1538-4365/aab776 Citable link http://nrs.harvard.edu/urn-3:HUL.InstRepos:41504669 Terms of Use This article was downloaded from Harvard University’s DASH repository, and is made available under the terms and conditions applicable to Open Access Policy Articles, as set forth at http:// nrs.harvard.edu/urn-3:HUL.InstRepos:dash.current.terms-of- use#OAP Draft version January 30, 2018 Typeset using LATEX twocolumn style in AASTeX62 AAS WorldWide Telescope: Seamless, Cross-Platform Data Visualization Engine for Astronomy Research, Education, and Democratizing Data Philip Rosenfield,1 Jonathan Fay,1 Ronald K Gilchrist,1 Chenzhou Cui,2 A. David Weigel,3 Thomas Robitaille,4 Oderah Justin Otor,1 and Alyssa Goodman5 1American Astronomical Society 1667 K St NW Suite 800 Washington, DC 20006, USA 2National Astronomical Observatories, Chinese Academy of Sciences 20A Datun Road, Chaoyang District Beijing, 100012, China 3Christenberry Planetarium, Samford University 800 Lakeshore Drive Birmingham, AL 35229, USA 4Aperio Software Ltd. Headingley Enterprise and Arts Centre, Bennett Road Leeds, LS6 3HN, United Kingdom 5Harvard Smithsonian Center for Astrophysics 60 Garden St. -
Information Summaries
TIROS 8 12/21/63 Delta-22 TIROS-H (A-53) 17B S National Aeronautics and TIROS 9 1/22/65 Delta-28 TIROS-I (A-54) 17A S Space Administration TIROS Operational 2TIROS 10 7/1/65 Delta-32 OT-1 17B S John F. Kennedy Space Center 2ESSA 1 2/3/66 Delta-36 OT-3 (TOS) 17A S Information Summaries 2 2 ESSA 2 2/28/66 Delta-37 OT-2 (TOS) 17B S 2ESSA 3 10/2/66 2Delta-41 TOS-A 1SLC-2E S PMS 031 (KSC) OSO (Orbiting Solar Observatories) Lunar and Planetary 2ESSA 4 1/26/67 2Delta-45 TOS-B 1SLC-2E S June 1999 OSO 1 3/7/62 Delta-8 OSO-A (S-16) 17A S 2ESSA 5 4/20/67 2Delta-48 TOS-C 1SLC-2E S OSO 2 2/3/65 Delta-29 OSO-B2 (S-17) 17B S Mission Launch Launch Payload Launch 2ESSA 6 11/10/67 2Delta-54 TOS-D 1SLC-2E S OSO 8/25/65 Delta-33 OSO-C 17B U Name Date Vehicle Code Pad Results 2ESSA 7 8/16/68 2Delta-58 TOS-E 1SLC-2E S OSO 3 3/8/67 Delta-46 OSO-E1 17A S 2ESSA 8 12/15/68 2Delta-62 TOS-F 1SLC-2E S OSO 4 10/18/67 Delta-53 OSO-D 17B S PIONEER (Lunar) 2ESSA 9 2/26/69 2Delta-67 TOS-G 17B S OSO 5 1/22/69 Delta-64 OSO-F 17B S Pioneer 1 10/11/58 Thor-Able-1 –– 17A U Major NASA 2 1 OSO 6/PAC 8/9/69 Delta-72 OSO-G/PAC 17A S Pioneer 2 11/8/58 Thor-Able-2 –– 17A U IMPROVED TIROS OPERATIONAL 2 1 OSO 7/TETR 3 9/29/71 Delta-85 OSO-H/TETR-D 17A S Pioneer 3 12/6/58 Juno II AM-11 –– 5 U 3ITOS 1/OSCAR 5 1/23/70 2Delta-76 1TIROS-M/OSCAR 1SLC-2W S 2 OSO 8 6/21/75 Delta-112 OSO-1 17B S Pioneer 4 3/3/59 Juno II AM-14 –– 5 S 3NOAA 1 12/11/70 2Delta-81 ITOS-A 1SLC-2W S Launches Pioneer 11/26/59 Atlas-Able-1 –– 14 U 3ITOS 10/21/71 2Delta-86 ITOS-B 1SLC-2E U OGO (Orbiting Geophysical -
This Boeing Team's Skills at Producing Delta IV Rocket Fairings Helped
t’s usually the tail end of the rocket that gets all the early atten- other work. But they’d jump at the chance to work together again. tion, providing an impressive fiery display as the spacecraft is Their story is one of challenges and solutions. And they attribute hurled into orbit. But mission success also depends on what’s their success to Lean+ practices and good old-fashioned teamwork. Ion top of the rocket: a piece of metal called the payload fairing “The team took it upon themselves to make an excellent that protects the rocket’s cargo during the sometimes brutal ride product,” said program manager Thomas Fung. “We had parts to orbital speed. issues and tool problems, but the guys really stepped up and took “There’s no room for error,” said Tracy Allen, Boeing’s manu- pride and worked through the issues.” facturing production manager for a Huntington Beach, Calif., team The aluminum fairing team went through a major transition that made fairings for the Delta IV. The fairing not only protects the when Boeing merged its Delta Program with Lockheed Martin’s payload from launch to orbit but also must jettison properly for Atlas Program to form United Launch Alliance in 2006. deployment of the satellite or spacecraft. “There were a lot of process changes in the transition phase Allen and his colleagues built the 65-foot-long (20-meter-long) because we were working with a new company,” Fung said. “We aluminum isogrid fairings for the Delta IV heavy-lift launch vehicle. had part shortages because of vendor issues, and that caused The design was based on 41 similar fairings Boeing made for the an impact to the schedule. -
Douglas Missile & Space Systems Division
·, THE THOR HISTORY. MAY 1963 DOUGLAS REPORT SM-41860 APPROVED BY: W.H.. HOOPER CHIEF, THOR SYSTEMS ENGINEERING AEROSPACE SYSTEMS ENGINEERING DOUGLAS MISSILE & SPACE SYSTEMS DIVISION ABSTRACT This history is intended as a quick orientation source and as n ready-reference for review of the Thor and its sys tems. The report briefly states the development of Thor, sur'lli-:arizes and chronicles Thor missile and booster launch inGs, provides illustrations and descriptions of the vehicle systcn1s, relates their genealogy, explains sane of the per fon:iance capabilities of the Thor and Thor-based vehicles used, and focuses attention to the exploration of space by Douelas Aircraf't Company, Inc. (DAC). iii PREFACE The purpose of The Thor History is to survey the launch record of the Thor Weapon, Special Weapon, and Space Systems; give a systematic account of the major events; and review Thor's participation in the military and space programs of this nation. The period covered is from December 27, 1955, the date of the first contract award, through May, 1963. V �LE OF CONTENTS Page Contract'Award . • • • • • • • • • • • • • • • • • • • • • • • • • 1 Background • • • • • • • • • • • • • • • • • • • • • • • • • • • • l Basic Or�anization and Objectives • • • • • • • • • • • • • • • • 1 Basic Developmenta� Philosophy . • • • • • • • • • • • • • • • • • 2 Early Research and Development Launches • • • ·• • • • • • • • • • 4 Transition to ICBM with Space Capabilities--Multi-Stage Vehicles . 6 Initial Lunar and Space Probes ••••••• • • • • • • • -
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. -
Atlas Launch System Mission Planner's Guide, Atlas V Addendum
ATLAS Atlas Launch System Mission Planner’s Guide, Atlas V Addendum FOREWORD This Atlas V Addendum supplements the current version of the Atlas Launch System Mission Plan- ner’s Guide (AMPG) and presents the initial vehicle capabilities for the newly available Atlas V launch system. Atlas V’s multiple vehicle configurations and performance levels can provide the optimum match for a range of customer requirements at the lowest cost. The performance data are presented in sufficient detail for preliminary assessment of the Atlas V vehicle family for your missions. This guide, in combination with the AMPG, includes essential technical and programmatic data for preliminary mission planning and spacecraft design. Interface data are in sufficient detail to assess a first-order compatibility. This guide contains current information on Lockheed Martin’s plans for Atlas V launch services. It is subject to change as Atlas V development progresses, and will be revised peri- odically. Potential users of Atlas V launch service are encouraged to contact the offices listed below to obtain the latest technical and program status information for the Atlas V development. For technical and business development inquiries, contact: COMMERCIAL BUSINESS U.S. GOVERNMENT INQUIRIES BUSINESS INQUIRIES Telephone: (691) 645-6400 Telephone: (303) 977-5250 Fax: (619) 645-6500 Fax: (303) 971-2472 Postal Address: Postal Address: International Launch Services, Inc. Commercial Launch Services, Inc. P.O. Box 124670 P.O. Box 179 San Diego, CA 92112-4670 Denver, CO 80201 Street Address: Street Address: International Launch Services, Inc. Commercial Launch Services, Inc. 101 West Broadway P.O. Box 179 Suite 2000 MS DC1400 San Diego, CA 92101 12999 Deer Creek Canyon Road Littleton, CO 80127-5146 A current version of this document can be found, in electronic form, on the Internet at: http://www.ilslaunch.com ii ATLAS LAUNCH SYSTEM MISSION PLANNER’S GUIDE ATLAS V ADDENDUM (AVMPG) REVISIONS Revision Date Rev No. -
A New Polarimeter to Study the Curl Component of the Cosmic Microwave Background Polarization
UNIVERSITA` DEGLI STUDI DI ROMA \LA SAPIENZA" Facolt`adi Scienze Matematiche Fisiche e Naturali A new polarimeter to study the curl component of the Cosmic Microwave Background polarization Tesi di Laurea Specialistica in Astronomia ed Astro¯sica Anno Accademico 2005/2006 Author Supervisor Lorenzo Moncelsi Prof. Paolo de Bernardis Register: 1071681 Co-supervisor Dott. Federico Nati Contents Introduzione 6 Introduction 10 1 The Hot Big Bang Model and the Inflation add-on 11 1.1 Introduction . 11 1.2 The Standard Cosmological Model . 11 1.3 The Unsolved Problems . 17 1.3.1 The flatness problem . 17 1.3.2 The horizons problem . 18 1.3.3 The absence of magnetic monopoles . 19 1.4 The Solution: Inflation . 20 1.5 The Physics of Inflation . 22 1.5.1 Scalar Fields . 22 1.5.2 Slow-Roll Approximation . 25 1.5.3 Exact Solutions . 26 1.5.4 Hamilton-Jacobi Formulation . 28 1.5.5 Reheating . 29 1.5.6 Scalar Fluctuations . 30 1.5.7 Tensor Fluctuations . 34 2 The Cosmic Microwave Background 37 2.1 Introduction . 37 2.2 Earth's Absolute Motion: The Dipole Anisotropy . 39 2.3 The Last Scattering Surface . 42 2.4 The Temperature Power Spectrum . 44 2.4.1 Physical E®ects at Recombination . 44 2.4.2 Statistical Treatment . 47 2.4.3 The Shape of the Spectrum . 49 2.5 Polarization . 54 2.5.1 Thomson Scattering at Recombination . 54 2.5.2 Statistical Treatment . 56 2.5.3 Quadrupole Anisotropy From Scalar Perturbations . 65 I 2.5.4 Quadrupole Anisotropy From Tensor Perturbations . -
The Hot and Energetic Universe
The Hot And Energetic Universe The Universe was always the final frontier of the Human quest for knowledge Through all its history, humanity has observed the sky trying to understand the Cosmos outside the limits of our planet Today, this effort has yielded significant results. Now we know that our sun is a typical star, which does not differ significantly from the other stars of the starry sky. We have discovered the planets of our Solar System and we have studied the conditions prevailing in them. We studied asteroids and comets and found their important role in the formation of planets. We understand the basic principles of the formation, the life and the death of stars. We have also discovered thousands of exoplanets orbiting other stars. We studied giant star clusters. We have discovered dense clouds of interstellar dust and gas where new stars are born continuously. We have managed to describe the gigantic complex of stars to which we belong. Our Galaxy. We realized that our Galaxy is not alone in the universe and that there are hundreds of billions of galaxies. We discovered that the universe of galaxies is extremely violent and in constant motion. Finally we found that the whole universe is in accelerating expansion and we are searching urgently for its origin. This quest is an epic journey towards knowledge, which abolish superstitions and defines human existence. Vehicles for the journey of humanity in the universe are scientific instruments called telescopes, which are installed at various observatories. Telescopes collect light. Their performance depends on the diameter of the lens or mirror used. -
Army Ballistic Missile Programs at Cape Canaveral 1953 – 1988
ARMY BALLISTIC MISSILE PROGRAMS AT CAPE CANAVERAL 1953 – 1988 by Mark C. Cleary 45th SPACE WING History Office TABLE OF CONTENTS Preface…………………………………………………… iii INTRODUCTION……………………………………… 1 REDSTONE……………………………………………… 15 JUPITER…………………………………………………. 44 PERSHING………………………………………………. 68 CONCLUSION………………………………………….. 90 ii Preface The United States Army has sponsored far fewer launches on the Eastern Range than either the Air Force or the Navy. Only about a tenth of the range’s missile and space flights can be attributed to Army programs, versus more than a third sponsored by each of the other services. Nevertheless, numbers seldom tell the whole story, and we would be guilty of a grave disservice if we overlooked the Army’s impressive achievements in the development of rocket- powered vehicles, missile guidance systems, and reentry vehicle technologies from the late 1940s onward. Several years of experimental flights were conducted at the White Sands Proving Ground before the Army sponsored the first two ballistic missile launches from Cape Canaveral, Florida, in July 1950. In June 1950, the Army moved some of its most important guided missile projects from Fort Bliss, Texas, to Redstone Arsenal near Huntsville, Alabama. Work began in earnest on the REDSTONE ballistic missile program shortly thereafter. In many ways, the early Army missile programs set the tone for the development of other ballistic missiles and range instrumentation by other military branches in the 1950s. PERSHING missile launches continued at the Cape in the 1960s, and they were followed by PERSHING 1A and PERSHING II launches in the 1970s and 1980s. This study begins with a summary of the major events leading up to the REDSTONE missile program at Cape Canaveral. -
(50000) Quaoar, See Quaoar (90377) Sedna, See Sedna 1992 QB1 267
Index (50000) Quaoar, see Quaoar Apollo Mission Science Reports 114 (90377) Sedna, see Sedna Apollo samples 114, 115, 122, 1992 QB1 267, 268 ap-value, 3-hour, conversion from Kp 10 1996 TL66 268 arcade, post-eruptive 24–26 1998 WW31 274 Archimedian spiral 11 2000 CR105 269 Arecibo observatory 63 2000 OO67 277 Ariel, carbon dioxide ice 256–257 2003 EL61 270, 271, 273, 274, 275, 286, astrometric detection, of extrasolar planets – mass 273 190 – satellites 273 Atlas 230, 242, 244 – water ice 273 Bartels, Julius 4, 8 2003 UB313 269, 270, 271–272, 274, 286 – methane 271–272 Becquerel, Antoine Henry 3 – orbital parameters 271 Biermann, Ludwig 5 – satellite 272 biomass, from chemolithoautotrophs, on Earth 169 – spectroscopic studies 271 –, – on Mars 169 2005 FY 269, 270, 272–273, 286 9 bombardment, late heavy 68, 70, 71, 77, 78 – atmosphere 273 Borealis basin 68, 71, 72 – methane 272–273 ‘Brown Dwarf Desert’ 181, 188 – orbital parameters 272 brown dwarfs, deuterium-burning limit 181 51 Pegasi b 179, 185 – formation 181 Alfvén, Hannes 11 Callisto 197, 198, 199, 200, 204, 205, 206, ALH84001 (martian meteorite) 160 207, 211, 213 Amalthea 198, 199, 200, 204–205, 206, 207 – accretion 206, 207 – bright crater 199 – compared with Ganymede 204, 207 – density 205 – composition 204 – discovery by Barnard 205 – geology 213 – discovery of icy nature 200 – ice thickness 204 – evidence for icy composition 205 – internal structure 197, 198, 204 – internal structure 198 – multi-ringed impact basins 205, 211 – orbit 205 – partial differentiation 200, 204, 206, -
Atlas V Cutaway Poster
ATLAS V Since 2002, Atlas V rockets have delivered vital national security, science and exploration, and commercial missions for customers across the globe including the U.S. Air Force, the National Reconnaissance Oice and NASA. 225 ft The spacecraft is encapsulated in either a 5-m (17.8-ft) or a 4-m (13.8-ft) diameter payload fairing (PLF). The 4-m-diameter PLF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction with vertical split-line longerons. The Atlas V 400 series oers three payload fairing options: the large (LPF, shown at left), the extended (EPF) and the extra extended (XPF). The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur upper stage and the spacecraft, which separates using a debris-free pyrotechnic actuating 200 ft system. Payload clearance and vehicle structural stability are enhanced by the all-aluminum forward load reactor (FLR), which centers the PLF around the Centaur upper stage and shares payload shear loading. The Atlas V 500 series oers 1 three payload fairing options: the short (shown at left), medium 18 and long. 1 1 The Centaur upper stage is 3.1 m (10 ft) in diameter and 12.7 m (41.6 ft) long. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle. It uses a single RL10 engine producing 99.2 kN (22,300 lbf) of thrust.