Satellite Scoreboard . . . US and USSR
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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 -
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. -
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. -
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. -
The Advanced Cryogenic Evolved Stage (ACES)- a Low-Cost, Low-Risk Approach to Space Exploration Launch
The Advanced Cryogenic Evolved Stage (ACES)- A Low-Cost, Low-Risk Approach to Space Exploration Launch J. F. LeBar1 and E. C. Cady2 Boeing Phantom Works, Huntington Beach CA 92647 Space exploration top-level objectives have been defined with the United States first returning to the moon as a precursor to missions to Mars and beyond. System architecture studies are being conducted to develop the overall approach and define requirements for the various system elements, both Earth-to-orbit and in-space. One way of minimizing cost and risk is through the use of proven systems and/or multiple-use elements. Use of a Delta IV second stage derivative as a long duration in-space transportation stage offers cost, reliability, and performance advantages over earth-storable propellants and/or all new stages. The Delta IV second stage mission currently is measured in hours, and the various vehicle and propellant systems have been designed for these durations. In order for the ACES to have sufficient life to be useful as an Earth Departure Stage (EDS), many systems must be modified for long duration missions. One of the highest risk subsystems is the propellant storage Thermal Control System (TCS). The ACES effort concentrated on a lower risk passive TCS, the RL10 engine, and the other subsystems. An active TCS incorporating a cryocoolers was also studied. In addition, a number of computational models were developed to aid in the subsystem studies. The high performance TCS developed under ACES was simulated within the Delta IV thermal model and long-duration mission stage performance assessed. -
ULA Rideshare Capabilities for Providing Low-Cost Access to Space
United Launch Alliance Rideshare Capabilities for Providing Low-Cost Access to Space Keith Karuntzos United Launch Alliance PO Box 3788, MIS C4102 Centennial, CO 80155-3788 303-269-5499 [email protected] Abstract-United Launch Alliance (ULA) has a long history of REFERENCES ••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 9 providing launch services to high-value payloads for a variety BIOGRAPHY •••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 9 of customers, including the US Department of Defense, the National Reconnaissance Office, NASA, and commercial customers. These missions have deployed a wide variety of capabilities into Earth orbit and beyond, such as navigation, 1. VVHAT IS RIDESHARE? communication, R&D, observation, and science, all which have Since the dawn of the space age, spacecraft have often provided us with a tremendous amount of knowledge about Earth and our solar system. The majority of these spacecraft shared launch services with one another while being has been launched as primary payloads, and used the full delivered into space. This approach has normally been done capability of the launch vehicle; yet there is a lower-cost to support spacecraftmuch smaller than the primary payload alternative for achieving similar mission objectives: rideshare. it is launching with. By designing launch services in this manner, spacecraft operators were able to deliver more Rideshare is the approach of sharing available launch vehicle payloads to orbit for a fraction of the cost of a full-up launch performance and volume margins with two or more spacecraft service. that would otherwise go underutilized by the spacecraft community. This allows spacecraft customers the opportunity This method of launching multiple payloads into orbit on a to get their spacecraft to orbit and beyond in an inexpensive single launch vehicle is called rideshare. -
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. -
Evolved Expendable Launch Operations at Cape Canaveral, 2002-2009
EVOLVED EXPENDABLE LAUNCH OPERATIONS AT CAPE CANAVERAL 2002 – 2009 by Mark C. Cleary 45th SPACE WING History Office PREFACE This study addresses ATLAS V and DELTA IV Evolved Expendable Launch Vehicle (EELV) operations at Cape Canaveral, Florida. It features all the EELV missions launched from the Cape through the end of Calendar Year (CY) 2009. In addition, the first chapter provides an overview of the EELV effort in the 1990s, summaries of EELV contracts and requests for facilities at Cape Canaveral, deactivation and/or reconstruction of launch complexes 37 and 41 to support EELV operations, typical EELV flight profiles, and military supervision of EELV space operations. The lion’s share of this work highlights EELV launch campaigns and the outcome of each flight through the end of 2009. To avoid confusion, ATLAS V missions are presented in Chapter II, and DELTA IV missions appear in Chapter III. Furthermore, missions are placed in three categories within each chapter: 1) commercial, 2) civilian agency, and 3) military space operations. All EELV customers employ commercial launch contractors to put their respective payloads into orbit. Consequently, the type of agency sponsoring a payload (the Air Force, NASA, NOAA or a commercial satellite company) determines where its mission summary is placed. Range officials mark all launch times in Greenwich Mean Time, as indicated by a “Z” at various points in the narrative. Unfortunately, the convention creates a one-day discrepancy between the local date reported by the media and the “Z” time’s date whenever the launch occurs late at night, but before midnight. (This proved true for seven of the military ATLAS V and DELTA IV missions presented here.) In any event, competent authorities have reviewed all the material presented in this study, and it is releasable to the general public. -
Two-Stage, High-Altitude Rocket with Internal Skeleton Design Entered in Advance Category of 7Th ESRA IREC
Two-Stage, High-Altitude Rocket with Internal Skeleton Design Entered in Advance Category of 7th ESRA IREC Samuel S. Bowman1, Kevin J. Byrne2, Allen Capatina3, Aliki S. Loper-Leddy4, and Joshua A. Van Schoyck5 California Polytechnic State University, San Luis Obispo, CA, 93407 A high-altitude, two-stage rocket was designed, built, and entered in the advanced category of the 7th Annual Experimental Sounding Rocket Association (ESRA) Intercollegiate Rocketry Engineering Competition (IREC). The rocket, called AJAKS, featured an internal skeleton made of carbon fiber rods, and a combination of plywood, carbon, and aluminum bulkheads. Loads were driven through the internal structure, with an outer skin tube providing an aerodynamic surface. A unique separation device was developed to ensure proper stage separation. The competition required the rocket to carry a 10-lb payload, which was chosen by the team to consist of an IMU and data logging computer for recording the descent profile, a CubeSat test unit, and a digital video recorder. Prior to the competition launch, AJAKS was test launched on May 5th in the Mojave at the Friends of Amateur Rocketry (FAR) launch facility. During the test launch AJAKS suffered a PIRM malfunction and the main parachute did not deploy. Following the test launch, the second stage of the rocket was rebuilt with a stronger payload configuration. The ESRA IREC was held on June 21st to the 24th. AJAKS was launched on the 23rd and during ascent the second stage became unstable and reached an altitude of only 6,000 ft. Both stages suffered damage upon landing. Nomenclature A = reference area (inches2) CNα = normal force coefficient (unitless) cp = center of pressure location relative to nosecone tip (inches) E = elastic modulus (psi) I = area moment of inertia (inches2) L = length of the rocket (inches) Pcr = critical load for buckling (pounds) Subscripts b = first stage s = second stage total = first and second stage I. -
N AS a Facts
National Aeronautics and Space Administration NASA’s Launch Services Program he Launch Services Program (LSP) manufacturing, launch operations and rockets for launching Earth-orbit and Twas established at Kennedy Space countdown management, and providing interplanetary missions. Center for NASA’s acquisition and added quality and mission assurance in In September 2010, NASA’s Launch program management of expendable lieu of the requirement for the launch Services (NLS) contract was extended launch vehicle (ELV) missions. A skillful service provider to obtain a commercial by the agency for 10 years, through NASA/contractor team is in place to launch license. 2020, with the award of four indefinite meet the mission of the Launch Ser- Primary launch sites are Cape Canav- delivery/indefinite quantity contracts. The vices Program, which exists to provide eral Air Force Station (CCAFS) in Florida, expendable launch vehicles that NASA leadership, expertise and cost-effective and Vandenberg Air Force Base (VAFB) has available for its science, Earth-orbit services in the commercial arena to in California. and interplanetary missions are United satisfy agencywide space transporta- Other launch locations are NASA’s Launch Alliance’s (ULA) Atlas V and tion requirements and maximize the Wallops Flight Facility in Virginia, the Delta II, Space X’s Falcon 1 and 9, opportunity for mission success. Kwajalein Atoll in the South Pacific’s Orbital Sciences Corp.’s Pegasus and facts The principal objectives of the LSP Republic of the Marshall Islands, and Taurus XL, and Lockheed Martin Space are to provide safe, reliable, cost-effec- Kodiak Island in Alaska. Systems Co.’s Athena I and II.