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Preface Patrick Besha, Editor Alexander Macdonald, Editor in The
EARLY DRAFT - NASAWATCH.COM/SPACEREF.COM Preface Patrick Besha, Editor Alexander MacDonald, Editor In the next decade, NASA will seek to expand humanity’s presence in space beyond the International Space Station in low-Earth orbit to a new habitation platform orbiting the moon. By the late 2020’s, astronauts will live and work far deeper in space than ever before. The push to cis-lunar orbit is part of a stepping-stone approach to extend our reach to Mars and beyond. This decision to explore ever farther destinations is a familiar pattern in the history of American space exploration. Another major pattern with historical precedent is the transition from public sector exploration to private sector commercialization. After the government has developed and demonstrated a capability in space, whether it be space-based communications or remote sensing, the private sector has realized its market potential. As new companies establish a presence, the government withdraws from the market. In 2015, we are once again at a critical stage in the development of space. The most successful long-term human habitation in space, orbiting the Earth continuously since 1998, is the International Space Station. Currently at the apex of its capabilities and the pinnacle of state-of-the-art space systems, it was developed through the investments and labors of over a dozen nations and is regularly re-supplied by cargo delivery services. Its occupants include six astronauts and numerous other organisms from Earth’s ecosystems from bacteria to plants to rats. Research is conducted on the spacecraft from hundreds of organizations worldwide ranging from academic institutions to large industrial companies and from high-tech start-ups to high-school science classes. -
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 -
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. -
Preparation of Papers for AIAA Technical Conferences
DUKSUP: A Computer Program for High Thrust Launch Vehicle Trajectory Design & Optimization Spurlock, O.F.I and Williams, C. H.II NASA Glenn Research Center, Cleveland, OH, 44135 From the late 1960’s through 1997, the leadership of NASA’s Intermediate and Large class unmanned expendable launch vehicle projects resided at the NASA Lewis (now Glenn) Research Center (LeRC). One of LeRC’s primary responsibilities --- trajectory design and performance analysis --- was accomplished by an internally-developed analytic three dimensional computer program called DUKSUP. Because of its Calculus of Variations-based optimization routine, this code was generally more capable of finding optimal solutions than its contemporaries. A derivation of optimal control using the Calculus of Variations is summarized including transversality, intermediate, and final conditions. The two point boundary value problem is explained. A brief summary of the code’s operation is provided, including iteration via the Newton-Raphson scheme and integration of variational and motion equations via a 4th order Runge-Kutta scheme. Main subroutines are discussed. The history of the LeRC trajectory design efforts in the early 1960’s is explained within the context of supporting the Centaur upper stage program. How the code was constructed based on the operation of the Atlas/Centaur launch vehicle, the limits of the computers of that era, the limits of the computer programming languages, and the missions it supported are discussed. The vehicles DUKSUP supported (Atlas/Centaur, Titan/Centaur, and Shuttle/Centaur) are briefly described. The types of missions, including Earth orbital and interplanetary, are described. The roles of flight constraints and their impact on launch operations are detailed (such as jettisoning hardware on heating, Range Safety, ground station tracking, and elliptical parking orbits). -
Centaur D-1A Pamphlet (1973)
• l:Intf.LN3~ UO!S!A!O 9:JedsoJ8t/ J!eAUOJ ''o'l:I3N3~ S:::ml\l'o'NAC ... ) Imagination has been the hallmark of the Cen taur program since its inception. Centaur was the vehicle selected to satisfy man's quest for knowledge in space. Already it has sent Survey or to probe the moon's surface. Mariner to chart the planet Mars, the Orbiti ng Astronomical Observatory to scan the stars without inter ference from the earth's atmosphere, and Pioneer to Jupiter and beyond. Centaur will also be called upon to launch other spacecraft to continue to unlock the secrets of the planets, such as Mariner for Venus and Mercury in 1973, Viking Orbiter/Lander spacecraft to Mars in 1975, and advanced Mariners to Jupiter and Saturn in 1977. Centaur has not only flown scientific missions but also ones with application for solving more tangible problems, such as Applications Tech nology Satellites and the Intelsat communica tions satellite. Centaur has also been chosen to deliver domestic and military communication satellites to synchronous orbit beginning in 1975. Because man's curiosity will never be satisfied, Convair Aerospace stands ready to respond to the challenges of tomorrow with the same imag inative design and quality craftsmanship embod ied in Centaur. K. E. Newton Vice President & Program Director Launch Vehicle Programs CONTENTS INTRODUCTION Introduction A little over a decade ago, Centaur began the first evolutionary steps from conventional Centaur Structure and Major Systems 3 Structure 4 rocketry to the high-energy-fueled vehicles of Propulsion 5 oxygen/hydrogen. Centaur faced numerous Reaction Control 6 problems, many of them demanding solutions Guidance 7 beyond the then current state of the art. -
Aeronautics and Space Report of the President
Aeronautics and Space Report of the President 1971 Activities NOTE TO READERS: ALL PRINTED PAGES ARE INCLUDED, UNNUMBERED BLANK PAGES DURING SCANNING AND QUALITY CONTROL CHECK HAVE BEEN DELETED Aeronautics and Space Report of the President 197 I Activities i W Executive Office of the President National Aeronautics and Space Council Washington, D.C. 20502 PRESIDENT’S MESSAGE OF TRANSMITTAL To the Congress of the United States: I am pleased to transmit herewith a report of our national progress in aero- nautics and space activities during 1971. This report shows that we have made forward strides toward each of the six objectives which I set forth for a balanced space program in my statement of March 7, 1970. Aided by the improvements we have made in mobility, our explorers on the moon last summer produced new, exciting and useful evidence on the structure and origin of the moon. Several phenomena which they uncovered are now under study. Our unmanned nearby observation of Mars is similarly valuable and significant for the advancement of science. During 1971, we gave added emphasis to aeronautics activities which contribute substantially to improved travel conditions, safety and security, and we gained in- creasing recognition that space and aeronautical research serves in many ways to keep us in the forefront of man’s technological achievements. There can be little doubt that the investments we are now making in explora- tions of the unknown are but a prelude to the accomplishments of mankind in future generations. THEWHITE HOUSE, March 1972 iii Table of Contents Page Page I . Progress Toward U.S. -
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. -
Deep Space Chronicle Deep Space Chronicle: a Chronology of Deep Space and Planetary Probes, 1958–2000 | Asifa
dsc_cover (Converted)-1 8/6/02 10:33 AM Page 1 Deep Space Chronicle Deep Space Chronicle: A Chronology ofDeep Space and Planetary Probes, 1958–2000 |Asif A.Siddiqi National Aeronautics and Space Administration NASA SP-2002-4524 A Chronology of Deep Space and Planetary Probes 1958–2000 Asif A. Siddiqi NASA SP-2002-4524 Monographs in Aerospace History Number 24 dsc_cover (Converted)-1 8/6/02 10:33 AM Page 2 Cover photo: A montage of planetary images taken by Mariner 10, the Mars Global Surveyor Orbiter, Voyager 1, and Voyager 2, all managed by the Jet Propulsion Laboratory in Pasadena, California. Included (from top to bottom) are images of Mercury, Venus, Earth (and Moon), Mars, Jupiter, Saturn, Uranus, and Neptune. The inner planets (Mercury, Venus, Earth and its Moon, and Mars) and the outer planets (Jupiter, Saturn, Uranus, and Neptune) are roughly to scale to each other. NASA SP-2002-4524 Deep Space Chronicle A Chronology of Deep Space and Planetary Probes 1958–2000 ASIF A. SIDDIQI Monographs in Aerospace History Number 24 June 2002 National Aeronautics and Space Administration Office of External Relations NASA History Office Washington, DC 20546-0001 Library of Congress Cataloging-in-Publication Data Siddiqi, Asif A., 1966 Deep space chronicle: a chronology of deep space and planetary probes, 1958-2000 / by Asif A. Siddiqi. p.cm. – (Monographs in aerospace history; no. 24) (NASA SP; 2002-4524) Includes bibliographical references and index. 1. Space flight—History—20th century. I. Title. II. Series. III. NASA SP; 4524 TL 790.S53 2002 629.4’1’0904—dc21 2001044012 Table of Contents Foreword by Roger D. -
Desind Finding
NATIONAL AIR AND SPACE ARCHIVES Herbert Stephen Desind Collection Accession No. 1997-0014 NASM 9A00657 National Air and Space Museum Smithsonian Institution Washington, DC Brian D. Nicklas © Smithsonian Institution, 2003 NASM Archives Desind Collection 1997-0014 Herbert Stephen Desind Collection 109 Cubic Feet, 305 Boxes Biographical Note Herbert Stephen Desind was a Washington, DC area native born on January 15, 1945, raised in Silver Spring, Maryland and educated at the University of Maryland. He obtained his BA degree in Communications at Maryland in 1967, and began working in the local public schools as a science teacher. At the time of his death, in October 1992, he was a high school teacher and a freelance writer/lecturer on spaceflight. Desind also was an avid model rocketeer, specializing in using the Estes Cineroc, a model rocket with an 8mm movie camera mounted in the nose. To many members of the National Association of Rocketry (NAR), he was known as “Mr. Cineroc.” His extensive requests worldwide for information and photographs of rocketry programs even led to a visit from FBI agents who asked him about the nature of his activities. Mr. Desind used the collection to support his writings in NAR publications, and his building scale model rockets for NAR competitions. Desind also used the material in the classroom, and in promoting model rocket clubs to foster an interest in spaceflight among his students. Desind entered the NASA Teacher in Space program in 1985, but it is not clear how far along his submission rose in the selection process. He was not a semi-finalist, although he had a strong application. -
555/Of 474- 70
555/of 474- 70/ A PERSPECTIVE ON THE USE OF STORABLE PROPELLANTS FOR FUTURE SPACE VEHICLE PROPULSION William C. Boyd and Warren L. Brasher NASA, Johnson Space Center 0 O"0 Houston, Texas 0 ABSTRACT Propulsion system configurations for future NASA and DOD space initiatives are driven by the continually emerging new mission requirements. These initiatives cover an extremely wide range of mission scenarios, from unmanned planetary pro- grams, to manned lunar and planetary programs, to Earth-oriented ('Mission to Planet Earth) programs, and they are in addition to existing and future require- ments for near-Eirth missions such as to geosynchronous earth orbit (GEO). Increasing space transportation costs, and anticipated high costs associated with space-basing of future vehicles, necessitate consideration of cost-effective and easily maintainable configurations which maximize the use of ex-Isting technologies and assets, and use budgetary resources effectively. System design considerations associated with the use of storable propellants to fill these needs are presented. Comparisons in areas such as ccrrplexity, performance, flexibility, maintainabili- ty, and technology status are made for earth and space storable propellants, cluding nitrogen tetroxide/monomethylhydrazine and LOX/monomethylhydrazine. INTRODUCTION As the nation approaches the next century, some very harsh realities mist be faced, and some equally important decisions will be made. The economic and progranrnatic realities of space flight, and of space vehicle development and oper- ation, have been forced home. We have learned that space systems are expensive and conplex, require a long time to develop, and are allowed very little margin for error. In spite of these realities, however, we know that doing business in space in the future is going to require significant advances in orbital capability over what is currently available. -
Characterization of Spacecraft Materials Using Reflectance Spectroscopy
Characterization of spacecraft materials using reflectance spectroscopy Jacqueline A. Reyes University of Texas at El Paso-Jacobs JETS Contract, El Paso, TX 79968 Darren Cone University of Texas at El Paso, El Paso, TX 79968 ABSTRACT Materials interact with light in a unique manner due to their individual elemental composition. Elements emit different light energies that fall within the electromagnetic spectrum, therefore corresponding to a specified wavelength per element. The reflectance spectrum produced from common spacecraft materials can be used to assist with remote orbital debris material identification techniques and can be further related to debris albedo and size. Materials used in aerospace design, such as aluminum alloys, stainless steels, ceramics, silicone paints, and solar cells, have been substantially characterized using reflectance spectroscopic techniques. An Analytical Spectral Device (ASD) was utilized to perform characterization on various spacecraft and rocket body structures by producing a spectrum relatively unique to a material from its properties in response to light. The materials used as specimen for this investigation specifically belong to a Titan IIIC Transtage test article rocket body, stainless steel radar calibration spheres, and solar cells used to construct a Hughes/Boeing HS-376 spacecraft. The spectrum results of said materials are presented in the subsequent work to enhance current spectroscopic data of interest within aerospace and orbital debris communities. 1. INTRODUCTION The space industry has succeeded in launching various spacecraft into Earth orbit to explore the nature of our space environment. This originated with the launch of the first satellite, Sputnik, on October 4, 1957 [1]. Since then, multiple space missions have been executed, leaving our near-Earth space environment populated with spacecraft.