GRAB and POPPY: America's Early
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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 ••••••• • • • • • • • -
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. -
Copyrighted Material
1 Introduction to Space Electronic Reconnaissance Geolocation 1.1 Introduction With the rapid development of aerospace technology, space has gradually become the strategic commanding point for defending national security and providing benefits. As the electronic reconnaissance satellite is able to acquire the full-time, all-weather, large-area, detailed, near real-time battlefield information (such as force deployment, military equipment, and operation information), it has become a powerful way to acquire information and plays an important role in ensuring information superiority [1, 2]. In the early 1960s, the United States launched the first general electronic reconnaissance satellites in the world – Grab and Poppy – to collect electronic intelligence (ELINT) on Soviet air defense radar signals. Intelligence from Grab and Poppy provided the location and capabilities of Soviet radar sites and ocean surveillance information to the US Navy and for use by the US Air Force. This effort provided significant ELINT support to US forces throughout the war in Vietnam [3]. Space electronic reconnaissance (SER) refers to the process in which signals from various electromagnetic transmitters are intercepted with the help of man-made satellites, and then features of signal are analyzed, contents of signal are extracted, and the position of transmit- ters are located [1–5]. The main tasks for space reconnaissance includes: intercepting signals from various transmitting sources such as radars, communication devices, navigation beacons, and identification -
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. -
National Reconnaissance Office Review and Redaction Guide
NRO Approved for Release 16 Dec 2010 —Tep-nm.T7ymqtmthitmemf- (u) National Reconnaissance Office Review and Redaction Guide For Automatic Declassification Of 25-Year-Old Information Version 1.0 2008 Edition Approved: Scott F. Large Director DECL ON: 25x1, 20590201 DRV FROM: NRO Classification Guide 6.0, 20 May 2005 NRO Approved for Release 16 Dec 2010 (U) Table of Contents (U) Preface (U) Background 1 (U) General Methodology 2 (U) File Series Exemptions 4 (U) Continued Exemption from Declassification 4 1. (U) Reveal Information that Involves the Application of Intelligence Sources and Methods (25X1) 6 1.1 (U) Document Administration 7 1.2 (U) About the National Reconnaissance Program (NRP) 10 1.2.1 (U) Fact of Satellite Reconnaissance 10 1.2.2 (U) National Reconnaissance Program Information 12 1.2.3 (U) Organizational Relationships 16 1.2.3.1. (U) SAF/SS 16 1.2.3.2. (U) SAF/SP (Program A) 18 1.2.3.3. (U) CIA (Program B) 18 1.2.3.4. (U) Navy (Program C) 19 1.2.3.5. (U) CIA/Air Force (Program D) 19 1.2.3.6. (U) Defense Recon Support Program (DRSP/DSRP) 19 1.3 (U) Satellite Imagery (IMINT) Systems 21 1.3.1 (U) Imagery System Information 21 1.3.2 (U) Non-Operational IMINT Systems 25 1.3.3 (U) Current and Future IMINT Operational Systems 32 1.3.4 (U) Meteorological Forecasting 33 1.3.5 (U) IMINT System Ground Operations 34 1.4 (U) Signals Intelligence (SIGINT) Systems 36 1.4.1 (U) Signals Intelligence System Information 36 1.4.2 (U) Non-Operational SIGINT Systems 38 1.4.3 (U) Current and Future SIGINT Operational Systems 40 1.4.4 (U) SIGINT -
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. -
National Reconnaissance Office (NRO) Mandatory Declassification Review (MDR) Log, 2011-2016
Description of document: National Reconnaissance Office (NRO) Mandatory Declassification Review (MDR) Log, 2011-2016 Requested date: 22-October-2016 Released date: 22-November-2016 Posted date: 05-December-2016 Source of document: Mandatory Declassification Review Request NRO National Reconnaissance Office COMM-IMSO-IRRG 14675 Lee Road Chantilly, VA 20151-1715 The governmentattic.org web site (“the site”) is noncommercial and free to the public. The site and materials made available on the site, such as this file, are for reference only. The governmentattic.org web site and its principals have made every effort to make this information as complete and as accurate as possible, however, there may be mistakes and omissions, both typographical and in content. The governmentattic.org web site and its principals shall have neither liability nor responsibility to any person or entity with respect to any loss or damage caused, or alleged to have been caused, directly or indirectly, by the information provided on the governmentattic.org web site or in this file. The public records published on the site were obtained from government agencies using proper legal channels. Each document is identified as to the source. Any concerns about the contents of the site should be directed to the agency originating the document in question. GovernmentAttic.org is not responsible for the contents of documents published on the website. NATIONAL RECONNAISSANCE OFFICE 14675 Lee Road Chantilly, VA 20151 -1715 22 November 2016 This is in response to your letter dated 22 October 2016 and received in the National Reconnaissance Office (NRO) on 2 November 2016. Pursuant to Executive Order 13526, Section 3.6, you requested a mandatory declassification review of "the Mandatory Declassification Review (MDR) Log maintained by the National Reconnaissance Office .. -
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. -
MIT Japan Program Working Paper 01.10 the GLOBAL COMMERCIAL
MIT Japan Program Working Paper 01.10 THE GLOBAL COMMERCIAL SPACE LAUNCH INDUSTRY: JAPAN IN COMPARATIVE PERSPECTIVE Saadia M. Pekkanen Assistant Professor Department of Political Science Middlebury College Middlebury, VT 05753 [email protected] I am grateful to Marco Caceres, Senior Analyst and Director of Space Studies, Teal Group Corporation; Mark Coleman, Chemical Propulsion Information Agency (CPIA), Johns Hopkins University; and Takashi Ishii, General Manager, Space Division, The Society of Japanese Aerospace Companies (SJAC), Tokyo, for providing basic information concerning launch vehicles. I also thank Richard Samuels and Robert Pekkanen for their encouragement and comments. Finally, I thank Kartik Raj for his excellent research assistance. Financial suppport for the Japan portion of this project was provided graciously through a Postdoctoral Fellowship at the Harvard Academy of International and Area Studies. MIT Japan Program Working Paper Series 01.10 Center for International Studies Massachusetts Institute of Technology Room E38-7th Floor Cambridge, MA 02139 Phone: 617-252-1483 Fax: 617-258-7432 Date of Publication: July 16, 2001 © MIT Japan Program Introduction Japan has been seriously attempting to break into the commercial space launch vehicles industry since at least the mid 1970s. Yet very little is known about this story, and about the politics and perceptions that are continuing to drive Japanese efforts despite many outright failures in the indigenization of the industry. This story, therefore, is important not just because of the widespread economic and technological merits of the space launch vehicles sector which are considerable. It is also important because it speaks directly to the ongoing debates about the Japanese developmental state and, contrary to the new wisdom in light of Japan's recession, the continuation of its high technology policy as a whole. -
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 E W S L E T T
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Increasing Launch Rate and Payload Capabilities
Aerial Launch Vehicles: Increasing Launch Rate and Payload Capabilities Yves Tscheuschner1 and Alec B. Devereaux2 University of Colorado, Boulder, Colorado Two of man's greatest achievements have been the first flight at Kitty Hawk and pushing into the final frontier that is space. Air launch systems aim to combine these great achievements into a revolutionary way to deliver satellites, cargo and eventually people into space. Launching from an aircraft has many advantages, including the ability to launch at any inclination and from above bad weather, which could delay ground launches. While many concepts for launching rockets from an airplane have been developed, very few have made it past the drawing board. Only the Pegasus and, to a lesser extent, SpaceShipOne have truly shown the feasibility of such a system. However, a recent push for rapid, small payload to orbit launches by the military and a general need for cheaper, heavy lift options are leading to an increasing interest in air launch methods. In order for the efficiency and flexibility of the system to be realized, however, additional funding and research are necessary. Nomenclature ALASA = airborne launch assist space access ALS = air launch system DARPA = defense advanced research project agency LEO = low Earth orbit LOX = liquid oxygen RP-1 = rocket propellant 1 MAKS = Russian air launch system MECO = main engine cutoff SS1 = space ship one SS2 = space ship two I. Introduction W hat typically comes to mind when considering launching people or satellites to space are the towering rocket poised on the launch pad. These images are engraved in the minds of both the public and scientists alike.