“Angara” Launch Vehicle Family Concept, Development Status and Operational Plans

Total Page:16

File Type:pdf, Size:1020Kb

“Angara” Launch Vehicle Family Concept, Development Status and Operational Plans “ANGARA” LAUNCH VEHICLE FAMILY CONCEPT, DEVELOPMENT STATUS AND OPERATIONAL PLANS A. Medvedev, A. Kuzin, E. Motorny, Khrunichev Space Center, Russia, B. Katorgin, NPO Energomash, Russia Abstract “ANGARA” BACKGROUND The design of “Angara” launch vehi- cles family is based on the concept of com- Development of the “Angara” launch mon (so called universal) rocket module of system is one of the most impotent projects the first stage. Full scale development of the undertaken by Khrunichev Space Center. "Angara" space complex has been carried The history of the “Angara” project, out for several years by Khrunichev Space main technological features and innovations Center. The first test flight of this new gen- as well as status of the program and future eration launchers is scheduled to occur in plans were repeatedly presented in mass the last quarter of 2003 from Plesetsk cos- media and in the papers of Khrunichev’s modrome. “Angara 1.1" lightweight launch representatives at various international fo- rums and conferences. For example, the pa- vehicle will be the first to lift into orbit. th Practical realization of modularity concept pers [1,2] were presented at the 37 Session goes through incorporating of the first stage of Scientific and Technical Sub-Comminute Universal Rocket Module (URM-1) in all on the Peaceful Uses of Outer Space Affairs the launchers of the family, either as com- in Vienna in 2000 and at the First Summit plete first stages of lightweight class launch on the Space Transportation Business in vehicles, or as core units and strap-on Paris (1999). boosters of intermediate and heavy launch- As it was described earlier the “An- ers. The second stage has two different vari- gara” family comprises from four main con- ants: “Rockot” LV derived “Breeze-KM” figurations of launch vehicles (Fig. 1). The upper stage for “Angara 1.1" launcher and centerpiece of the Khrunichev’s modular newly developed Universal Rocket Module concept is the URM-1, which is a common (URM-2) second stage for all other configu- unit (with some variations) for all the rations. Descriptions of the URM-1/ URM-2 launchers of the family. Besides the URM-2 propulsion units, which are based on the second stage is used in all the launchers ex- oxygen/kerosene RD-191 and RD-0124A cept “Angara 1.1”. Application of flight- main rocket engines correspondently, are proven upper stages, adapters and payload given in the paper. Programmatic aspects fairings is also one of important principles including development test plans and of “Angara” design concept. schedules of the initial operation phase are In connection with the subject of this discussed as well. Symposium, it is reasonable to look through The "Baikal" first stage reusable specific technological solutions, which were fly-back booster, which is based on the incorporated into the design of above men- URM-1 technology, is aimed to increase the tioned universal rocket modules of the first operational efficiency of the "Angara" and second stages. launchers family. Improvements of the UNIVERSAL MODULES DESIGN RD-191 booster main engine transforming it The URM-1 (Fig. 2) was developed as into reusable design are presented. a first stage of the “Angara 1.1/1.2” light- New design features and concepts, weight class launch vehicles and as a core which have been introduced in "Angara" unit and strap-on boosters of the intermedi- space complex, will increase the Russian ate “Angara A3” and heavy “Angara A5” space launch industry's competitiveness in launch vehicles. Design parameters of the the international commercial launch ser- URM-1 are the result of comprehensive vices market and assured free access to trade-off studies performed by Khrunichev space from national territory. Space Center in 1995…1997. Studies were confidence in reliability and operational aimed to find the way of meeting different functionality of the new engine. sets of requirements stemming from differ- The RD-191 is currently undergoing ences in foreseen operation modes of LVs. hot firing stand tests (Fig. 3). The pneu- Based on the found technical solutions matic/hydraulic diagram of this engine and Khrunichev’s developers came to a conclu- its performances are shown in Fig. 4. The sion that the optimum design should be an RD-191 is an oxygen/kerosene engine, oxygen/ kerosene universal booster module which is designed in the framework of gen- characterized by: erator gas after-burning concept with a ca- • diameter D=2,9 m, pability of combustion chamber’s deflection • length L=25,105 m, in a Cardan suspension. An ignition is pro- • loaded propellant mass ∼120 t vided by a chemical method, by feeding into and equipped with single main rocket en- the combustion chamber special starting gine having a thrust of about 200 tons. fuel, which is self-ignited when in contact These parameters led to the robust solution with liquid oxygen (oxidizer). in wide ranges of operational requirements Besides a mode of throttling down to and forecasted international market changes. 30% of nominal thrust, the engine allows The main engine should have a capability of also a short-time burning in a mode of en- thrust vector control (TVC) as well as a ca- hanced thrust (up to 5% of nominal level) in pability to function during a long time in the emergency situations. mode of lowered thrust (down to 30% of TVC in channels of pitch and jaw is nominal level) for its applications in core provided by deflections of combustion units of intermediate/heavy launchers. The chamber in a Cardan suspension. Besides last requirement appeared due to a pro- this, the engine can feed a generator gas for longed time core booster’s run in flight in running of nozzles providing control on a comparison with strap-on boosters. Addi- roll channel. This feature of the engine is tional engine’s requirements covered high crucial for control of the first stages of light- level of reliability, which should be con- weight launch vehicles and of the core firmed before its installation into the boosters of intermediate/heavy launch vehi- URM-1, and introduction of effective sys- cles. The engine fulfills two additional func- tem for in-flight safety assurance, which tions: should reduce the flight risk coursed by en- • heating of gas (helium) for a pres- gine’s malfunction. surization of propellant tanks and These requirements were met by the • bleeding of fuel after a pump for RD-191 (191M) single-chamber liquid- running of hydraulic actuators providing propellant rocket engine, which was offered deflections of combustion chamber and by the Russian NPO “Energomash”. aerodynamic rudders. RD-191 engine was developed as one of Engine's design includes pipelines, derivatives of the just existing and success- valves and fittings of automatics and con- fully operated RD-171 four-chamber rocket trol, that provide functioning of the engine engine. This engine has not only the highest in various modes. The engine RD-191 is level of thrust in the world, but has a very also equipped with sensors for telemetry high perfection of design. Another deriva- measurements of the burning parameters in tive of the RD-171, the two-chamber RD- flight and with an equipment of monitoring/ 180 engine has just proved itself success- emergency protection system. The last sys- fully on the U.S. “Atlas III” launch vehicle. tem is intended for countering emergency An adoption of such an important compo- situations during the flight. nent as the combustion chamber from the The RD-191 engine was just “fitted” RD-171 and RD-180 engines allowed not to the universal rocket module. In March only to decrease development cost and dura- 1999 its first mock-up/technological sample tion for the RD-191 but also to enhance a was delivered to Khrunichev and was in- stalled on the engineering mock-up of the URM-1 — a first stage of the “Angara 1.1” The first step to enhance the URM-1 launch vehicle (Fig. 5). The engineering reliability is to incorporate into its design mock-up of this launcher was shown at the subsystems, units and aggregates that allow Le-Bourget Airshow in 1999 (Fig. 6). Since repeated running before the beginning of Airshow it passed a variety of on-ground irreversible processes (e.g., take-off of the development/technological tests. launcher from a launch pad). This approach A general design layout of the univer- provides an opportunity to perform the pre- sal rocket module equipped with the RD- launch (on pad) tests including those that 191 engine is shown in Fig. 7. Differences are carried out in order to detect and to between the variants of URM-1 design and eliminate possible failures of on-board sys- operations are caused by the position of tems and units without a replacement of the URM-1 in LV configuration. Additional whole launcher. aerodynamic rudders for roll control equip Delivery procedures of the RD-191 the URMs that are used as first stages of engine envisage comprehensive control/ small launchers. The URMs, which are used technological tests including hot firing ac- as strap-on boosters, have no roll control ceptance test of each fabricated RD-191 en- nozzles. Both upper mentioned URMs func- gine. After test is performed the engine un- tion in flight for 210…240 seconds in al- dergoes a cycle of technological works most nominal level of thrust (except for legs (without reassembling) that includes a ther- of ignition and shut-down). In case URMs mal/vacuum processing of fuel pipelines, a are used as core boosters of intermedi- removal of soot from outside surfaces and a ate/heavy launch vehicles they perform at replacement of ampoules with the starting throttling mode (30% of nominal thrust) fuel.
Recommended publications
  • Measurements of Π , K , P and ¯P Spectra in Proton-Proton
    EUROPEAN ORGANISATION FOR NUCLEAR RESEARCH (CERN) Submitted to: Eur. Phys. J. C CERN-EP-2017-066 September 28, 2017 Measurements of π±,K±, p and ¯p spectra in proton-proton interactions at 20, 31, 40, 80 and 158 GeV=c with the NA61/SHINE spectrometer at the CERN SPS The NA61/SHINE Collaboration Measurements of inclusive spectra and mean multiplicities of π±,K±, p and p¯ produced in =c inelasticp p+p interactions at incident projectile momenta of 20, 31, 40, 80 and 158 GeV ( s = 6.3, 7.7, 8.8, 12.3 and 17.3 GeV, respectively) were performed at the CERN Super Proton Synchrotron using the large acceptance NA61/SHINE hadron spectrometer. Spectra are presented as function of rapidity and transverse momentum and are compared to predictions of current models. The measurements serve as the baseline in the NA61/SHINE study of the properties of the onset of deconfinement and search for the critical point of strongly interacting matter. arXiv:1705.02467v2 [nucl-ex] 27 Sep 2017 © 2017 CERN for the benefit of the NA61/SHINE Collaboration. Reproduction of this article or parts of it is allowed as specified in the CC-BY-4.0 license. 1. Introduction This paper presents experimental results on inclusive spectra and mean multiplicities of π±,K±, p and p¯ produced in inelastic p+p interactions at 20, 31, 40, 80 and 158 GeV=c. The measurements were performed by the multi-purpose NA61/SHINE experiment [1, 2] at the CERN Super Proton Synchrotron (SPS). The new measurements complement previously published results from the same datasets on π− production [3] obtained without particle identification as well as on fluctuations of charged particles [4].
    [Show full text]
  • Human Spaceflight Plans of Russia, China and India
    Presentation to the ASEB Committee on NASA Technology Roadmaps Panel on Human Health and Surface Exploration June 1, 2011 by Marcia S. Smith Space and Technology Policy Group, LLC Russia Extensive experience in human spaceflight First animal in space (1957), first man in space (1961), first woman in space (1963), first spacewalk (1965), first space station (1971) Seven successful space stations (Salyut 1, 3, 4, 5, 6, 7 and Mir) before partnering in International Space Station (ISS) No people beyond low Earth orbit (LEO), however For earth orbit, continues to rely on Soyuz, first launched in 1967, but upgraded many times and is key to ISS operations Designed space shuttle, Buran, but launched only once in automated mode (no crew) in 1988 06-01-2011 2 Russia (2) Existing reliable launch vehicles Proton is largest: 21 tons to LEO; 5.5 tons to geostationary transfer orbit (GTO) Attempts to build Saturn V-equivalent in 1960s and 1970s failed (N1 failed four times in four attempts 1969-1972) Energiya booster in 1980s only flew twice (1987 with Polyus and 1988 with Buran). Abandoned for financial reasons. Was 100 tons to LEO; 18-20 tons to GTO; 32 tons to lunar trajectory. RD-170 engines for Energiya’s strap-ons live on today in other forms for Zenit, Atlas V, and Angara (under development) 06-01-2011 3 Russia (3) Robotic planetary space exploration mixed Excellent success at – Moon (Luna and Lunokhod series, plus Zond circumlunar flights) Venus (Venera series) Halley’s Comet (Vega 1 and 2—also Venus) Jinxed at Mars More than a dozen failures in 1960s - 1970s Partial success with Phobos 2 in 1988 (Phobos 1 failed) Mars 96 failed to leave Earth orbit Phobos-Grunt scheduled for later this year; designed as sample return from Phobos (includes Chinese orbiter) 06-01-2011 4 Russia (4) Grand statements over decades about sending people to the Moon and Mars, but never enough money to proceed.
    [Show full text]
  • Proton Accident with GLONASS Satellites
    3/29/2018 Proton accident with GLONASS satellites Previous Proton mission: SES­6 PICTURE GALLERY A Proton rocket with the Block D 11S861 stage and 813GLN34 payload firing shortly before liftoff on July 2, 2013. Upcoming book on space exploration Read more and watch videos in: Site map Site update log About this site About the author The ill­fated Proton rocket lifts off on July 2, 2013, at 06:38:21.585 Moscow Time (July 1, 10:38 p.m. EDT). The rocket crashed approximately 32.682 seconds later, Roskosmos said on July 18, 2013. Mailbox Russia's Proton crashes with a trio of navigation satellites SUPPORT THIS SITE! Published: July 1; updated: July 2, 3, 4, 5, 9, 11, 15, 18, 19; 23; Aug. 11 Related pages: Russia's Proton rocket crashed less than a minute after its liftoff from Baikonur, Kazakhstan. A Proton­M vehicle No. 53543 with a Block DM­03 (11S­86103) upper stage lifted off as scheduled from Pad No. 24 at Site 81 (launch complex 8P­882K) in Baikonur Cosmodrome on July 2, 2013, at 06:38:21.585 Moscow Time (on July 1, 10:38 p.m. EDT). The rocket started veering off course right after leaving the pad, deviating from the vertical path in various RD­253/275 engines directions and then plunged to the ground seconds later nose first. The payload section and the upper stage were sheered off the vehicle moments before it impacted the ground and exploded. The flight lasted no more than 30 seconds. Searching for details: The Russian space agency's ground processing and launch contractor, TsENKI, was broadcasting the launch live and captured the entire process of the vehicle's disintegration and its crash.
    [Show full text]
  • Igor AFANASYEV, Dmitry VORONTSOV Cosmonautics | Event
    cosmonautics | event Andrey Morgunov Igor AFANASYEV, Dmitry VORONTSOV AANGARA’SNGARA’S FFIRSTIRST BBLASTOFFLASTOFF At 16.04 hrs Moscow time on 9 July 2014, the Plesetsk space launch centre saw the launching facility in February 2014 to the first launch of the Angara-1.2PP launch vehicle of the advanced space rocket practice its fuelling and the nose fairing was family being developed by the Khrunichev state space research and production fitted on the rocket in March. The successful ground tests were followed by the prelaunch centre. The maiden blastoff conducted as part of the Angara flight test programme preparations. was aimed at testing the solutions embodied in the design of the URM-1 and URM-2 The date of the launch was put off for versatile rocket modules and the Angara’s launch and technical facilities as well. 27 June 2014 due to extra checks required. In this connection, orbiting an actual spacecraft had not been considered, with On 9 June, Khrunichev hosted a session of an inseparable full-scale mock-up used as payload. The flight was suborbital to the Chief Designers Council, dedicated to prevent cluttering near-Earth orbit with space junk. the preparation of the Angara to its flight tests. The session pronounced the rocket fit To say the Angara’s first launch had been In spite of the hurdles, the developer, for the trials. anticipated for a long time would be an nevertheless, got in the stretch with the Angara The LV had been taken out of the assembly understatement: it was slated for 2005 under programme.
    [Show full text]
  • Building and Maintaining the International Space Station (ISS)
    / Building and maintaining the International Space Station (ISS) is a very complex task. An international fleet of space vehicles launches ISS components; rotates crews; provides logistical support; and replenishes propellant, items for science experi- ments, and other necessary supplies and equipment. The Space Shuttle must be used to deliver most ISS modules and major components. All of these important deliveries sustain a constant supply line that is crucial to the development and maintenance of the International Space Station. The fleet is also responsible for returning experiment results to Earth and for removing trash and waste from the ISS. Currently, transport vehicles are launched from two sites on transportation logistics Earth. In the future, the number of launch sites will increase to four or more. Future plans also include new commercial trans- ports that will take over the role of U.S. ISS logistical support. INTERNATIONAL SPACE STATION GUIDE TRANSPORTATION/LOGISTICS 39 LAUNCH VEHICLES Soyuz Proton H-II Ariane Shuttle Roscosmos JAXA ESA NASA Russia Japan Europe United States Russia Japan EuRopE u.s. soyuz sL-4 proton sL-12 H-ii ariane 5 space shuttle First launch 1957 1965 1996 1996 1981 1963 (Soyuz variant) Launch site(s) Baikonur Baikonur Tanegashima Guiana Kennedy Space Center Cosmodrome Cosmodrome Space Center Space Center Launch performance 7,150 kg 20,000 kg 16,500 kg 18,000 kg 18,600 kg payload capacity (15,750 lb) (44,000 lb) (36,400 lb) (39,700 lb) (41,000 lb) 105,000 kg (230,000 lb), orbiter only Return performance
    [Show full text]
  • The European Launchers Between Commerce and Geopolitics
    The European Launchers between Commerce and Geopolitics Report 56 March 2016 Marco Aliberti Matteo Tugnoli Short title: ESPI Report 56 ISSN: 2218-0931 (print), 2076-6688 (online) Published in March 2016 Editor and publisher: European Space Policy Institute, ESPI Schwarzenbergplatz 6 • 1030 Vienna • Austria http://www.espi.or.at Tel. +43 1 7181118-0; Fax -99 Rights reserved – No part of this report may be reproduced or transmitted in any form or for any purpose with- out permission from ESPI. Citations and extracts to be published by other means are subject to mentioning “Source: ESPI Report 56; March 2016. All rights reserved” and sample transmission to ESPI before publishing. ESPI is not responsible for any losses, injury or damage caused to any person or property (including under contract, by negligence, product liability or otherwise) whether they may be direct or indirect, special, inciden- tal or consequential, resulting from the information contained in this publication. Design: Panthera.cc ESPI Report 56 2 March 2016 The European Launchers between Commerce and Geopolitics Table of Contents Executive Summary 5 1. Introduction 10 1.1 Access to Space at the Nexus of Commerce and Geopolitics 10 1.2 Objectives of the Report 12 1.3 Methodology and Structure 12 2. Access to Space in Europe 14 2.1 European Launchers: from Political Autonomy to Market Dominance 14 2.1.1 The Quest for European Independent Access to Space 14 2.1.3 European Launchers: the Current Family 16 2.1.3 The Working System: Launcher Strategy, Development and Exploitation 19 2.2 Preparing for the Future: the 2014 ESA Ministerial Council 22 2.2.1 The Path to the Ministerial 22 2.2.2 A Look at Europe’s Future Launchers and Infrastructure 26 2.2.3 A Revolution in Governance 30 3.
    [Show full text]
  • Commercialization of Russian Technology in Cooperation with American Companies
    Stanford University CISAC Center for International Security and Cooperation The Center for International Security and Cooperation, part of Stanford University’s Institute for International Studies, is a multidisciplinary community dedicated to research and train- ing in the field of international security. The Center brings together scholars, policymakers, scientists, area specialists, members of the business community, and other experts to examine a wide range of international security issues. Center for International Security and Cooperation Stanford University Encina Hall Stanford, California 94305-6165 (415) 723-9625 http://www.stanford.edu/group/CISAC/ Commercialization of Russian Technology in Cooperation with American Companies David Bernstein June 1999 David Bernstein, an engineering research associate at Stanford University’s Center for Inter- national Security and Cooperation, participates in the Center’s Project on Industrial Restruc- turing and the Political Economy in Russia. The opinions expressed here are those of the author and do not represent positions of the Center, its supporters, or Stanford University. © 1999 by the Board of Trustees of the Leland Stanford Junior University ISBN 0-935371-53-2 i ii Contents I. Introduction 1 II. Background 5 III. Case Studies Introduction to Case Studies 17 Air Products & Chemicals, Incorporated 19 Boeing 21 Corning, Incorporated 27 Energia, Ltd. 29 NPO Energomash 33 FMC 37 General Electric 41 The State Scientific Research Institute of Aviation Systems (GosNIIAS) 43 Karpov Institute
    [Show full text]
  • 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 .
    [Show full text]
  • 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.
    [Show full text]
  • Russia Missile Chronology
    Russia Missile Chronology 2007-2000 NPO MASHINOSTROYENIYA | KBM | MAKEYEV DESIGN BUREAU | MITT | ZLATOUST MACHINE-BUILDING PLANT KHRUNICHEV | STRELA PRODUCTION ASSOCIATION | AAK PROGRESS | DMZ | NOVATOR | TsSKB-PROGRESS MKB RADUGA | ENERGOMASH | ISAYEV KB KHIMMASH | PLESETSK TEST SITE | SVOBODNYY COSMODROME 1999-1996 KRASNOYARSK MACHINE-BUILDING PLANT | MAKEYEV DESIGN BUREAU | MITT | AAK PROGRESS NOVATOR | SVOBODNYY COSMODROME Last update: March 2009 This annotated chronology is based on the data sources that follow each entry. Public sources often provide conflicting information on classified military programs. In some cases we are unable to resolve these discrepancies, in others we have deliberately refrained from doing so to highlight the potential influence of false or misleading information as it appeared over time. In many cases, we are unable to independently verify claims. Hence in reviewing this chronology, readers should take into account the credibility of the sources employed here. Inclusion in this chronology does not necessarily indicate that a particular development is of direct or indirect proliferation significance. Some entries provide international or domestic context for technological development and national policymaking. Moreover, some entries may refer to developments with positive consequences for nonproliferation 2007-2000: NPO MASHINOSTROYENIYA 28 August 2007 NPO MASHINOSTROYENIYA TO FORM CORPORATION NPO Mashinostroyeniya is set to form a vertically-integrated corporation, combining producers and designers of various supply and support elements. The new holding will absorb OAO Strela Production Association (PO Strela), OAO Permsky Zavod Mashinostroitel, OAO NPO Elektromekhaniki, OAO NII Elektromekhaniki, OAO Avangard, OAO Uralskiy NII Kompositsionnykh Materialov, and OAO Kontsern Granit-Elektron. While these entities have acted in coordination for some time, formation of the new corporation has yet to be finalized.
    [Show full text]
  • Of S.P. Korolev Rocket and Space Public Corporation Energia for 2013
    OF S.P. KOROLEV ROCKET AND SPACE PUBLIC CORPORATION ENERGIA FOR 2013 This Annual Report of S.P. Korolev Rocket and Space Public Corporation Energia (also hereinafter called “OAO RSC Energia”, “RSC Energia”, “the Corporation”) by the 2013 performance is drawn up in accordance with the RF Government Decree No 1214 as of December 31, 2010 “On Improvement of the Procedure for Management of Open Joint-Stock Companies Whose Stock is in Federal Ownership and Federal State Unitary Enterprises” with due regard for the requirements set forth in the Order issued by the RF Federal Financial Markets Service No 11-46/pz-n as of October 4, 2011 “On Approval of the Provision on Information Disclosure of Issuers of Registered Securities”. This Annual Report was preliminarily approved by RSC Energia’s Board of Directors on April 29, 2014. Minutes No10 as of May 6, 2014. Accuracy of the data contained in this Annual Report was confirmed by RSC Energia’s Auditing Committee Report as of April 17, 2014. 2 TABLE OF CONTENTS KEY PERFORMANCE INDICATORS ........................................................................... 6 ON CORPORATION ACTIVITIES ................................................................................. 8 Corporation background ................................................................................................................................8 Corporation structure (its participation in subsidiary and affiliated companies) ...........................................9 Information about purchase and sale contracts for
    [Show full text]
  • SOYUZ THROUGH the AGES the R-7 Rocket That Led to the Family of Soyuz Vehicles Launching Today Lifted Off for the First Time Onfeb
    RUSSIAN SPACE SOYUZ THROUGH THE AGES The R-7 rocket that led to the family of Soyuz vehicles launching today lifted off for the first time onFeb. 17, 1959. The last launch, on Dec. 27, 2018, was number 1,898. Irene Klotz and Maxim Pyadushkin Vostochny Cosmodrome anufactured by the Progress Rocket Space Center in Sama- Evolution of Soyuz-Family Launch Vehicles ra, Russia, the medium-lift expendable booster originally was used for Soviet-era human space missions and later became the R-7 Soyuz Soyuz-L workhorse for the country’s civilian and military space programs. M 1957 First launch of the ICBM (SS-6 1966-76 (32 launches, 1970-71 (three launches, Sapwood) that served as a basis for including 30 successful, all successful, The first rocket officially named Soyuz was launched in Soviet/Russian launch vehicles from Baikonur) from Baikonur) 1966 and has since flown 1,050 times, of which 1,023 were including the Soyuz family successful. Production of Soyuz rockets peaked in the early Soyuz 1980s at about 60 vehicles per year. Medium-Class Launch Vehicle Russia began offering Soyuz launch services internationally in the mid-1980s through Glavkosmos, a commercial entity set up to sell Soviet rocket and space technologies. Manufacturer: Progress Rocket Space Soyuz-U/-U2 Soyuz-M Center, Samara, Russia In 1996, Russia created Starsem, a joint venture (35% ArianeGroup, 25% Roscosmos, 25% RKTs Progress, 15% 1991 Breakup of the 1973-2017 1971-76 (eight launches, Soviet Union, (859 launches, including all successful, from Plesetsk) Dimensions Arianespace) that had exclusive rights to provide commercial launch services on Soyuz launch vehicles.
    [Show full text]