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Nuclear, Missile Space Digest
1 Nuclear, MissileNuclear, Missile & Space Digest & Space Digest Volume 11, Number 18 A Fortnightly Newsletter from the Indian Pugwash Society September 30, 2019 Convenor A. India “Imran Khan Hypes Kashmir, Personally Attacks PM Modi”: Ex-US Envoy Amb. Sujan R. Chinoy Chandrayaan 2 Completes Final In-Orbit Manoeuvre Before India’s Maiden Moon Landing On 7 Sept Russia plans to set up above 20 nuclear power units in India in next 20 years “India Will Not Balk At Using Strength To Defend Itself”: Rajnath Singh Explained: Chandrayaan-2, in perspective Lander ‘tilted’ not broken, says ISRO Modi should correct Vajpayee wrong on nuclear ‘no first use’: Diplomat Jaimini Bhagwati Chandrayaan 2: Nobel laureate entrusts Indian scientists, says ‘they will Executive Council soon master the setbacks of lunar mission’ Devices onboard Chandrayaan-2 orbiter gamechangers Cdr. (Dr.) Probal K. Ghosh Chandrayaan 2: Here’s how NASA is helping ISRO in reviving Air Marshal S. G. Inamdar Vikram Lander (Retd.) Dr. Roshan Khanijo B. China Amb. R. Rajagopalan China issues white paper on nuclear safety China Focus: China issues white paper on nuclear safety, stressing int’l Dr. Rajesh Rajagopalan cooperation Shri Dinesh Kumar US ban for nuclear firm harms own interests Yadvendra China to build lab for radioactive waste disposal China’s lunar rover travels over 284 meters on moon’s far side China sends H-6K bombers to Russia for strategic drills Chinese netizens encourage India’s lunar dream despite failure Implementation phase of China-funded Egyptian -
AMC-14 MO Final.Qxp 2/29/2008 1:15 PM Page 1
AMC-14 MO final.qxp 2/29/2008 1:15 PM Page 1 THE VEHICLE THE SATELLITE PROTON HISTORY PROTON www.ilslaunch.com Lead designer was Vladimir Chelomei, DESCRIPTION who designed it with the intention of creating a powerful rocket for both TOTAL HEIGHT military payloads and as a high- 56.2 m (184 ft) performance ICBM. The program GROSS LIFTOFF was changed, and the rocket WEIGHT was developed exclusively for 691,272 kg launching spacecraft. (1,523,565 lbm) First named UR-500, but PROPELLANT UDMH and N O adopted the name 2 4 “Proton,” which also was INITIAL LAUNCH the name of the first July 16, 1965 three payloads Proton-1 Spacecraft launched. PAYLOAD FAIRINGS Proton launched Russian There are multiple payload fair- ing designs presently qualified for interplanetary missions to flight, including standard commer- the Moon, Venus, Mars, and cial payload fairings developed specif- Halley’s Comet. ically to meet the needs of our Western customers. Proton launched the Salyut space stations, the Mir BREEZE M UPPER STAGE SATELLITE OPERATOR core segment and both The Breeze M is powered by one pump-fed gim- SES AMERICOM baled main engine that develops thrust of 19.6 kN the Zarya and Zvezda www.ses-americom.com (4,400 lbf). The Breeze M is composed of a central core modules for today’s and a jettisonable additional propellant tank. Inert mass of the SATELLITE MANUFACTURER International Space stage at liftoff is approximately 2,370 kg (5,225 lbm). The quan- Lockheed Martin Commercial Space Systems Station. tity of propellant carried is dependent on specific mission require- www.lmcommercialspace.com ments and is varied to maximize mission performance. -
The Technological and Commercial Expansion of Electric Propulsion in the Past 24 Years
The Technological and Commercial Expansion of Electric Propulsion in the Past 24 Years IEPC-2017-242 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology • Atlanta, Georgia • USA October 8 – 12, 2017 Dan Lev1, Roger M. Myers 2, Jonathan Kolbeck3 Michael Keidar3, Jose Gonzalez del Amo4, Wonho Choe5, Hiroyuki Koizumi6, Riccardo Albertoni7, Stephen Gabriel8, Ikkoh Funaki9…, William Hart10 1Rafael – Advanced Defense Systems, Haifa, Israel, 3102102, Israel 2Space Electric Propulsion Consultant, Seattle, WA, USA 3George Washington University, Washington D.C., USA 4European Space Agency (ESA), Noordwijk, Netherlands 5Korea Advanced Institute of Science and Technology (KAIST), Daejeon, South-Korea 6The University of Tokyo, Bunkyo-ku, Tokyo, 113-8654, Japan 7Airbus Defence and Space, Toulouse, France 8Mars Space Ltd., Southampton, UK 9Institute of Space and Astronautical Science / JAXA, Sagamihara, Kanagawa, 252-5210, Japan 10Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA, USA Abstract: These instructions give you guidelines for preparing papers for IEPC17. Use this document as a template if you are using Microsoft Word 6.0 or later. Otherwise, use this document as an instruction set. Define all symbols used in the abstract. Do not cite references in the abstract. The footnote on the first page should list the job title and email address for each author. I.Introduction N the hundred years since electric propulsion (EP) was originally conceived it has been developed by an I increasing number of research and industrial entities worldwide1. To date a myriad of technological subclasses of EP exist2,3, each at a different Technological Readiness Level (TRL), from basic notions of particle acceleration techniques to space proven applications. -
Global Satellite Communications Technology and Systems
International Technology Research Institute World Technology (WTEC) Division WTEC Panel Report on Global Satellite Communications Technology and Systems Joseph N. Pelton, Panel Chair Alfred U. Mac Rae, Panel Chair Kul B. Bhasin Charles W. Bostian William T. Brandon John V. Evans Neil R. Helm Christoph E. Mahle Stephen A. Townes December 1998 International Technology Research Institute R.D. Shelton, Director Geoffrey M. Holdridge, WTEC Division Director and ITRI Series Editor 4501 North Charles Street Baltimore, Maryland 21210-2699 WTEC Panel on Satellite Communications Technology and Systems Sponsored by the National Science Foundation and the National Aeronautics and Space Administration of the United States Government. Dr. Joseph N. Pelton (Panel Chair) Dr. Charles W. Bostian Mr. Neil R. Helm Institute for Applied Space Research Director, Center for Wireless Deputy Director, Institute for George Washington University Telecommunications Applied Space Research 2033 K Street, N.W., Rm. 304 Virginia Tech George Washington University Washington, DC 20052 Blacksburg, VA 24061-0111 2033 K Street, N.W., Rm. 340 Washington, DC 20052 Dr. Alfred U. Mac Rae (Panel Chair) Mr. William T. Brandon President, Mac Rae Technologies Principal Engineer Dr. Christoph E. Mahle 72 Sherbrook Drive The Mitre Corporation (D270) Communications Satellite Consultant Berkeley Heights, NJ 07922 202 Burlington Road 5137 Klingle Street, N.W. Bedford, MA 01730 Washington, DC 20016 Dr. Kul B. Bhasin Chief, Satellite Networks Dr. John V. Evans Dr. Stephen A. Townes and Architectures Branch Vice President Deputy Manager, Communications NASA Lewis Research Center and Chief Technology Officer Systems and Research Section MS 54-2 Comsat Corporation Jet Propulsion Laboratory 21000 Brookpark Rd. -
The Annual Compendium of Commercial Space Transportation: 2017
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY . -
Development of a Hydrazine Arcjet System Operating at 100 Volts Input Voltage
International Electric Propulsion Conference, October 2017, Atlanta, Georgia IEPC 2017-305 Development of a Hydrazine Arcjet System Operating at 100 Volts Input Voltage Dieter M. Zube1, Keith D. Goodfellow2, Chris Hearn3 Aerojet Rocketdyne Inc., Redmond, WA 98052, U.S.A. Abstract Since 1996, Aerojet Rocketdyne MR-510 hydrazine arcjet systems have provided North-South station keeping for more than 44 geostationary spacecraft. A typical system consists of four 2 kW arcjets, two of which can be operated simultaneously from a Power Conversion Unit (PCU) that includes three power converters in a three for two redundant arrangement. Over the last two years, the flexibility of the system was expanded by developing and qualifying a modern state of the art PCU for a 100 VDC spacecraft power bus. To set the stage, the paper summarizes the development and deployment history of hydrazine arcjet systems beginning in 1993. It discusses the changes and repeated system life tests which significantly expanded the flexibility and robustness of the arcjet system. The paper then describes the changes necessary to accommodate the new PCU with an input voltage of 100 VDC and a new communication protocol. While there were only a limited number of changes required for the thruster and its subcomponents, the PCU underwent a complete redesign. Aerojet Rocketdyne incorporated advances in design philosophy, electronic components, and materials to avoid component obsolescence while improving overall system reliability. 1. Hydrazine Arcjet System History propulsion systems was dormant until a Electric propulsion (EP) systems are usually development effort initiated by NASA and grouped by their primary acceleration industry in the early 1990s put hydrazine arcjets mechanism (electrothermal, electrostatic, and on the GE-Astro (now Lockheed Martin) Series electromagnetic), and there are six classical EP 7000 spacecraft bus in the form of the Aerojet thruster types: resistojets, arcjets, ion thrusters, Rocketdyne MR-508/509 hydrazine arcjet Hall current thrusters, Pulsed Plasma Thrusters system. -
Preparation of Papers for AIAA Technical Conferences
LEO to GEO (and Beyond) Transfers using High Power Solar Electric Propulsion (HP-SEP) IEPC-2017-396 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology • Atlanta, Georgia • USA October 8 – 12, 2017 Christopher S Loghry1 Moog Inc, Chatsworth, CA, 91311, USA Steven Oleson2, Jeffrey Woytach3, Michael Martini4, David Smith5, James Fittje6, John Gyekenyesi7, Anthony Colozza8, James Fincannon9, Aimee Bogner10, Robert Jones11, Thomas Packard12, Elizabeth Turnbull13 NASA Glenn Research Center, Cleveland, OH, 44135, USA Abstract: Rideshare, or Multi-Payload launch configurations, are becoming more and more commonplace but access to space is only one part of the overall mission needs. The ability for payloads to achieve their target orbits or destinations can still be difficult and potentially not feasible with on-board propulsion limitations. The High Power Solar Electric Propulsion (HP-SEP) Orbital Maneuvering Vehicle (OMV) provides transfer capabilities for both large and small payload in excess of what is possible with chemical propulsion. Leveraging existing secondary payload adapter technology like the ESPA provides a platform to support Multi-Payload launch and missions. When coupled with HP-SEP, meaning greater than 30 kW system power, very large delta-V maneuvers can be accomplished. The HP-SEP OMV concept is designed to perform a Low Earth Orbit to Geosynchronous Orbit (LEO- GEO) transfer of up to six payloads each with 300 kg mass. The OMV has enough capability to perform this 6 km/s maneuver and have residual capacity to extend an additional transfer from GEO to Lunar orbit. This high delta-V capability is achieved using state of the art 12.5 kW Hall Effect Thrusters (HET) coupled with high power “roll up” solar arrays. -
2001 Commercial Space Transportation Forecasts
2001 Commercial Space Transportation Forecasts Federal Aviation Administration's Associate Administrator for Commercial Space Transportation (AST) and the Commercial Space Transportation Advisory Committee (COMSTAC) May 2001 ABOUT THE ASSOCIATE ADMINISTRATOR FOR COMMERCIAL SPACE TRANSPORTATION (AST) AND THE COMMERCIAL SPACE TRANSPORTATION ADVISORY COMMITTEE (COMSTAC) The Federal Aviation Administration’s senior executives from the U.S. commercial Associate Administrator for Commercial Space space transportation and satellite industries, Transportation (AST) licenses and regulates U.S. space-related state government officials, and commercial space launch activity as authorized other space professionals. by Executive Order 12465, Commercial Expendable Launch Vehicle Activities, and the The primary goals of COMSTAC are to: Commercial Space Launch Act of 1984, as amended. AST’s mission is to license and • Evaluate economic, technological and regulate commercial launch operations to ensure institutional issues relating to the U.S. public health and safety and the safety of commercial space transportation industry property, and to protect national security and foreign policy interests of the United States • Provide a forum for the discussion of issues during commercial launch operations. The involving the relationship between industry Commercial Space Launch Act of 1984 and the and government requirements 1996 National Space Policy also direct the Federal Aviation Administration to encourage, • Make recommendations to the Administrator facilitate, and promote commercial launches. on issues and approaches for Federal policies and programs regarding the industry. The Commercial Space Transportation Advisory Committee (COMSTAC) provides Additional information concerning AST and information, advice, and recommendations to the COMSTAC can be found on AST’s web site, at Administrator of the Federal Aviation http://ast.faa.gov. -
Satcom for Net-Centric Warfare May 2012 Milsatmagazine
SatCom For Net-Centric Warfare May 2012 MilsatMagazine U.S.A.F.’s AEHF-2 Launch via ULA (cover photo) Competing For Space—AIAA Space Weather For Emergency Managers The Importance Of The Space Fence COMMAND CENTER General Thomas S. Moorman [Ret] Diego Paldao, NewSat Space Weather WGS + How The DoD’s MILSATCOM Vision Has Veered Off Track XipLink Discusses Optimization Space: Distruptive Challenges Industry Expansion, Exploration, Enthusiasm MilSatMagazine — May 2012 — Vol. 3, #2 Publishing Ops Silvano Payne ....................................Publisher + Writer Authors Hartley G. Lesser .................................Editorial Director Gunnery Sergeant Jennifer Antoine Pattie Waldt ......................................... Executive Editor Kyle Bond Jill Durfee ................. Sales Director, Editorial Assistant Staff Sergeant Andrew Caya Donald McGee ................................Production Manager Mike Conschafter Simon Payne ............................... Development Manager Tom Cristler, Colonel, U.S.A.F. [Ret.] Mike Antonovich ...............................Contributing Editor William J. Donahue, Lt. Gen. U.S.A.F. [Ret.] Maxime Baudry ................................Contributing Editor Elliot Holokauhi Pulham Chris Forrester ..................... Senior Contributing Editor Hartley Lesser Alan Gottlieb ........................ Senior Contributing Editor Doug Loverro, DISES, U.S.A.F. Bob Gough ............................ Senior Contributing Editor Ellen Pawlikowski, Lt. Gen., U.S.A.F. Richard Dutchik ...............................Contributing -
Uzay Sonda Roketġ Teknolojġlerġ Ve Uygulamalari
T.C. ULAġTIRMA DENĠZCĠLĠK VE HABERLEġME BAKANLIĞI UZAY SONDA ROKETĠ TEKNOLOJĠLERĠ VE UYGULAMALARI HAVACILIK VE UZAY TEKNOLOJĠLERĠ UZMANLIĞI TEZĠ Burak PEHLĠVAN, Havacılık ve Uzay Teknolojileri Uzman Yardımcısı Havacılık ve Uzay Teknolojileri Genel Müdürlüğü Mayıs 2018 Ankara T.C. ULAġTIRMA DENĠZCĠLĠK VE HABERLEġME BAKANLIĞI UZAY SONDA ROKETĠ TEKNOLOJĠLERĠ VE UYGULAMALARI HAVACILIK VE UZAY TEKNOLOJĠLERĠ UZMANLIĞI TEZĠ Burak PEHLĠVAN, Havacılık ve Uzay Teknolojileri Uzman Yardımcısı Havacılık ve Uzay Teknolojileri Genel Müdürlüğü DanıĢman Prof. Dr. OZAN TEKĠNALP Mayıs 2018 Ankara TEġEKKÜR Tez çalıĢmamda, deneyimi, bilgi birikimi ve zamanını esirgemeyen değerli danıĢmanım Sayın Prof. Dr. Ozan TEKĠNALP‟e, değerli zamanını ayırarak tezime önemli katkılar sağlayan Sayın Dr. Mehmet KARACA‟ya, bilgi ve desteklerini esirgemeyen değerli amirlerim ve çalıĢma arkadaĢlarıma, manevi destekleriyle beni hiçbir zaman yalnız bırakmayan aileme teĢekkürü bir borç bilirim. i BEYAN Bu belge ile sunduğum uzmanlık tezimdeki bütün bilgileri akademik kurallara ve etik davranıĢ ilkelerine uygun olarak toplayıp sunduğumu; ayrıca, bu kural ve ilkelerin gereği olarak, çalıĢmamda bana ait olmayan tüm veri, düĢünce ve sonuçları andığımı ve kaynağını gösterdiğimi beyan eder, tezimle ilgili yaptığım beyana aykırı bir durumun saptanması halinde ise, ortaya çıkacak tüm ahlaki ve hukuki sonuçlara katlanacağımı bildiririm. 30.05.2018 Burak PEHLĠVAN Havacılık ve Uzay Teknolojileri Uzman Yrd. ii ÖZET Tez, uzaya bağımsız eriĢimde önemli bir adımı oluĢturan sonda roketlerine -
GPS III to the Global Community
Bringing New Capabilities GPS III to the Global Community The next generation of GPS satellites — GPS III — is under development to bring improved performance and new capabilities to users around the globe. In this article, authors from the company designing and building those satellites describe the technical features and operational requirements of the GPS III that will produce these benefits. WILLARD MARQUIS, MICHAEL SHAW identifying similarities to and differences from earlier ver- LOCKHEED MARTIN SPACE SYSTEMS COMPANY sions of GPS satellites. We will highlight the basic subsystems of the GPS III SVs being built by Lockheed Martin, its navi- n May 2008, Lockheed Martin Space Systems Company gation payload subcontractor, ITT; communications payload received a contract from the U.S. Air Force to develop a subcontractor, General Dynamics; and numerous other new, third generation of GPS satellites. The GPS III space subcontractors. This article will also provide an overview of I vehicle (SV) has been designed (Figure 1) and is now the new signals and services on the GPS III SV, the SV simu- being built to bring new future capabilities to both military lators, and the assembly facility. and civil positioning, navigation, and timing (PNT) users throughout the globe. The Need for GPS III The GPS III SV critical design review (CDR) was success- GPS III is required to maintain the GPS constellation and fully completed in August 2010 — two months early. CDR improve PNT services to meet user demand in the future. marked the completion of the GPS III design phase, and the The GPS III capabilities, with the new L1C signal, higher production phase is now well under way with integration and signal power, greater accuracy, longer SV lifetime, and higher test to follow next year. -
Press Release
PRESS RELEASE SES Delivers Growth From Strong First Quarter Operational Performance Luxembourg, 24 April 2009 – SES S.A., the pre-eminent worldwide satellite operator, (Euronext Paris and Luxembourg Stock Exchange: SESG), reports on the financial performance in the three months to 31 March 2009. HIGHLIGHTS • Reported revenue of EUR 423.9 million, an increase of 8.4% over the prior year period • Recurring1 revenue of EUR 423.4 million, an increase of 3.1% over the prior year period • Reported EBITDA of EUR 308.9 million, an increase of 12.2% over the prior year period o EBITDA margin of 72.9% o infrastructure EBITDA margin improved to an industry-leading 84.4% • Recurring EBITDA of EUR 313.8 million, an increase of 6.0% over the prior year period • Operating profit of EUR 189.7 million, an increase of 14.7% over the prior year period • Profit of the group was EUR 121.8 million, an increase of 0.7% over the prior year period • Net debt / EBITDA stood at 3.06 times at the end of the period • Last twelve months weighted EPS rose by 1.0% to EUR 0.99 • Group transponder utilisation at 31 March was 79.6% or 880 of 1,105 commercially available transponders • After the period end, SES concluded a EUR 2.0 billion syndicated credit facility, thus enhancing SES' debt maturity profile Romain Bausch, President and CEO of SES, commented: "The evolution of our business during the first quarter of the year is in line with our expectations and business plan, underlining the inherent stability and growth potential of the SES business model.