DOCSLIB.ORG

Institute of Space Propulsion Lampoldshausen

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Institute of Space Propulsion Lampoldshausen 2017 - 2011 Part 1 Part Report Status Institute of Space Propulsion Lampoldshausen Status Report 2011-2017 Part 1 Institute of Space DLR Campus Site Management Propulsion Lampoldshausen Manager: Klaus Schäfer Director of Institute: Tobias Neff Prof. Dr. Stefan Schlechtriem Representatives IMB Branch Office of Institute Markus Prochazka Cornelia Bugge Departments Safety,Quality, Rocket Propulsion Engineering Test Facilities Propellants Technical Services Prof. Dr. Michael Klaus Schäfer Anja Frank Dr. Helmut Ciezki Michael Dommers Oschwald Head of Department Head of Department Head of Department Head of Department Head of Department Stand: 18.01.2016 Deutsches Zentrum für Luft- und Raumfahrt German Aerospace Center Institute of Space Propulsion Im Langen Grund 74239 Hardthausen Germany Tel.: +49 6298 28-0 Fax: +49 6298 28-190 www.dlr.de/la Cover Image: LOX/CH4test at test bench P3.2. Institute of Space Propulsion Institut für Raumfahrtantriebe Status Report 2011-2017 Status Report 2011-2017 DLR Lampoldshausen – Meeting the Demands of altitude testing is mandatory and represents a major Europe’s Spaceflight Program core competence in Lampoldshausen. All critical components and operating procedures for Space flight provides enormous benefits for scientific the new Vinci upper stage engine will be developed development and everyday life on earth. The fact is, it and tested in Lampoldshausen. In line with the goes unnoticed by most people although space flight German Space Strategy, DLR has defined specific and its fundamental research and services mean that research and development targets ranging from everyone can profit from the achievements of our system analysis of the engines, thrust chambers, modern society. Securing Europe’s access to space is nozzles, combustion, fuel management, ignition - crucial if Europe is to continue to play a leading role in particularly under vacuum conditions, cryo- space exploration and scientific progress. The further technology, all the way to testing, verification and development and operation of the European validation and thus qualification of the rocket engines Launcher Family is therefore vital. on the different test benches under settings The German Space Strategy, published on 1st De- characteristic of those found during launch and space cember 2010, clearly highlights that Lampoldshausen flight. is the pillar which supports Germany’s efforts to The completion of the new Upper Stage Test Facility guarantee access to space with the Ariane launcher will upgrade Lampoldshausen´s test portfolio; not family. Lampoldshausen’s unique high altitude fa- only rocket engines but complete upper stages of cilities ensure that Germany’s obligations within the rockets will then be certified in Lampoldshausen. European Launcher Community, namely systems responsibility for the old and new Ariane upper DLR Lampoldshausen is home to the Institute of stages, will be fulfilled. Space Propulsion and its five key departments: Test Facilities, Engineering, Rocket Propulsion, Propellants In as early as 1959 Lampoldshausen started working and Safety & Quality. very closely with the major French organizations involved in space propulsion and the Ariane pro- In view of the fact that potentially hazardous facilities grams. This teamwork is of fundamental importance are in operation on site, safety management plays a to the success of current and future European key role in the Institute. A safety office, site security launcher development projects. unit, site fire brigade, and medical service ensure the safety and protection of employees, facilities, and the The space company ASL also has a division on the environment alike during research and testing premises. In addition, various other companies and activities. organizations make use of the site’s services and test benches, thus contributing to cooperation on the In recent years, DLR Lampoldshausen has evolved to basis of a close-knit and mutually beneficial alliance. become a modern service provider currently incor- These include the European Space Agency (ESA) and porating all testing phases, i.e. from the provision of the French Space Agency Centre National d’Études et test benches and the operation of engines to the de Recherches Spatiales (CNES). recording and transmission of measurement data to the client. All of Lampoldshausen’s research and development programs directly support European rocket engine The Institute of Space Propulsion is one of a kind with development programs. Lampoldshausen has long its departments of Engineering, Test Operations on the been the main European development and testing one hand and scientific research on the other. It is site for all European liquid fuel rocket engines ranging able to handle the early stages of a development from attitude control engines (> 0,5 N) and apogee project all the way to final qualification, i.e. of a engines (>200 N) to large liquid hydrogen main stage certified rocket engine or stage. DLR Lam- engines (>1300 KN) such as Ariane´s main stage poldshausen can therefore proudly boast it is unique engine - the Vulcain. in that it is the only test site in the world which supplies research results from the early TRL 1 stage of At present and in the near future Lampoldshausen is an engine design through to full certification (TRL 9) dedicated to supporting Europe’s Ariane 6 program of the product. and as such the development of the new upper stage with the 180 kN, re-ignitable engine Vinci. High- It is well known that over the next few decades all launch vehicles will use chemical rocket engines. The Institute of Space Propulsion Preface 4 Status Report 2011-2017 key technology is combustion, and it is generally sources of qualified personnel for the European Space understood in the scientific community that Industry is another important goal of the Institute. regulating and managing exceptionally high power The Technology Transfer Center (TTZ) is a conglom- densities in rocket combustors is of peak importance. erate of various regional business associations which, The governing equations which are used to model the together with DLR Lampoldshausen, helps to improve multiple complex interacting processes in combustion the network of regional companies active in the field chambers are highly non-linear and therefore of science and industrial production. Clearly defined extremely difficult to balance out. While the synergies involving environment, health and safety, application of CFD or Computational Fluid Dynamics combustion, ignition, fuel management, cryo- and other improved modelling techniques used in technology and systems engineering exist and connection with compressor and turbine present opportunities for partnerships within and development paved the way to minimizing expensive outside of the space propulsion industry. The testing, keeping combustion phenomena under “H ORIZON” project has been initiated making use of control is still for the most part based on empirical 2 Lampoldshausen´s hydrogen infrastructure to foster analysis. Up to now only semi-empirical methods technology transfer as regards regenerative energies. have been used to design components like injectors, swirlers or the complete layout of a combustion Over the course of the last six decades, DLR in Lam- chamber. The only possibility to tune the chemical poldshausen has maintained its position amongst the combustion process is still solely by extensive testing forerunners in the European space flight program. in an environment of total quality control. This still Together with its partners in the aerospace industry, holds true for component tests on single injector the European Space Agency, the national agency, top elements as well as complete rocket engines with research organizations and universities world-wide, power head and nozzle. The Institute of Space the team in Lampoldshausen is making a vital Propulsion guarantees the maintenance of an contribution to developing and improving European infrastructure to develop and meet the requirements rocket propulsion systems and ensures the of today’s and tomorrow’s rocket engines. continuous success of European operational launchers. In addition to the unique features required by high altitude testing and cryogenic technology for the The DLR Institute for Space Propulsion in Lampolds- development and qualification of space propulsion hausen draws on competence and experience to systems, DLR Lampoldshausen develops and man- deliver qualified R&D results. ages the application of storable and gel propellants. The Institute for Space Propulsion coordinates the scientific and technical activities of the German Gel Prof. Dr.-Ing. Stefan Schlechtriem Technology Program. Over the last decade the search for rocket fuels (so-called “green propellants”) has been intensified to replace toxic products like German Aerospace Center hydrazine (see REACH). For this reason DLR Director Institute of Space Propulsion Lampoldshausen has added research in this field to its Im Langen Grund list of priorities. Lampoldshausen 74239 Hardthausen The training of space engineers and scientists plays a Germany major role in ensuring reliable, long-term support of European engine development programs. In 2005 DLR Lampoldshausen set up its DLR_School_Lab to address this important factor, a laboratory for young people where promising future generations of researchers conduct experiments under the guidance of experienced scientists and engineers. By implementing the DLR_Campus Lampoldshausen a further asset
Load more

Recommended publications
  • WARP Ten, 1992 Columbia College Chicago
    Columbia College Chicago Digital Commons @ Columbia College Chicago WARP ten Publications 2-1-1992 WARP ten, 1992 Columbia College Chicago Follow this and additional works at: https://digitalcommons.colum.edu/warpten Part of the Journalism Studies Commons This work is licensed under a Creative Commons Attribution-Noncommercial-No Derivative Works 4.0 License. Recommended Citation Columbia College Chicago, "WARP ten, 1992" (1992). WARP ten. 1. https://digitalcommons.colum.edu/warpten/1 This Book is brought to you for free and open access by the Publications at Digital Commons @ Columbia College Chicago. It has been accepted for inclusion in WARP ten by an authorized administrator of Digital Commons @ Columbia College Chicago. For more information, please contact [email protected]. A Science Newsletter of Columbia College Journalism Department Vol.I , No.I -~ Of Mars and Men By Robbie Robb the moon, a distance of 384,000km (239,000 miles) is but a three day voyage. A one-way trip to Mars, a distance of 56.4 million km. (35 million miles) rcquimi 280 days. The sheec The lure of the red planet has tantalized hlJIJUlllity for cen­ scope of the project thus demands a more expensive turies. Authors from H. G. Wells to Ray Bradbury havewriucn spacecraft. But traveling to Mars would also require more about life on Mars and coloni2ation of the planet. The Arnold resources at additional cosl Vast arnounlS of supplies, food. Schwanznegger movie, "Total Recall," portrayed a Martilln equipment, and fuel would be needed for a trip of this m11&­ world inhabited by tran.splanted earthlings. Now the idea of nitude.
    [Show full text]
  • Numerical Investigation of a 7-Element GOX/GCH4 Subscale Combustion Chamber
    DOI: 10.13009/EUCASS2017-173 7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) Numerical Investigation of a 7-Element GOX/GCH4 Subscale Combustion Chamber ? ? ? Daniel Eiringhaus †, Daniel Rahn‡, Hendrik Riedmann , Oliver Knab and Oskar Haidn‡ ?ArianeGroup Robert-Koch-Straße 1, 82024 Taufkirchen, Germany ‡Institute of Turbomachinery and Flight Propulsion (LTF), Technische Universität München (TUM) Boltzmannstr. 15, 85748 Garching, Germany [email protected] †Corresponding author Abstract For future liquid rocket engines methane has become the focus of several studies on alternative fuels in the western hemisphere. At ArianeGroup numerical simulation tools have been established as a powerful instrument in the design process. In order to achieve the same confidence level for CH4/O2 as for H2/O2 combustion, the applied numerical models have to be adapted and validated against sufficient test data. At the Chair of Space Propulsion at the Technical University of Munich (TUM) several combustion cham- bers have been designed and tests at different operating points have been conducted. In this paper one of these subscale combustion chambers with calorimetric cooling and seven shear coaxial injection elements running on gaseous methane and oxygen is used to examine ArianeGroup’s in-house tools for combustion chamber performance analysis. 1. Introduction Current development programs in many space-faring nations focus on launchers utilizing a propellant combination of liquid oxygen (LOX) and liquid methane (CH4). In Europe, hydrocarbons have been identified as an alternative fuel in the frame of the Future Launcher Preparatory Programme (FLPP).14, 23 Major industrial development of methane / oxy- gen rocket engines is ongoing in the United States at SpaceX with the Raptor engine (staged combustion), at Blue Origin with the BE-4 engine (staged combustion) and in Europe at ArianeGroup with the Prometheus engine (gas gen- erator).
    [Show full text]
  • Qualification Over Ariane's Lifetime
    r bulletin 94 — may 1998 Qualification Over Ariane’s Lifetime A. González Blázquez Directorate of Launchers, ESA, Paris M. Eymard Groupe Programme CNES/Arianespace, Evry, France Introduction Similarly, the RL10 engine on the Centaur stage The primary objectives of the qualification of the Atlas launcher has been the subject of an activities performed during the operational ongoing improvement programme. About 5000 lifetime of a launcher are: tests were performed before the first flight, and – to verify the qualification status of the vehicle 4000 during the subsequent ten years. – to resolve any technical problems relating to subsystem operations on the ground or in On-going qualification activities of a similar flight. nature were started for the Ariane-3 and 4 launchers in 1986, and for Ariane-5 in 1996. Before focussing on the European family of They can be classified into two main launchers, it is perhaps informative to review categories: ‘regular’ and ‘one-off’. just one or two of the US efforts in the area of solid and liquid propulsion in order to put the Ariane-3/4 accompanying activities Ariane-related activities into context. Regular activities These activities are mainly devoted to In principle, the development programme for a launcher ends with the verification of the qualification status of the qualification phase, after which it enters operational service. In various launcher subsystems. They include the practice, however, the assessment of a launcher’s reliability is a following work packages: continuing process and qualification-type activities proceed, as an – Periodic sampling of engines: one HM7 and extension of the development programme (as is done in aeronautics), one Viking per year, tested to the limits of the over the course of the vehicle’s lifetime.
    [Show full text]
  • High-Thrust In-Space Liquid Propulsion Stage: Storable Propellants
    View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Institute of Transport Research:Publications Space Propulsion 2014 – ID 2968378 High-Thrust in-Space Liquid Propulsion Stage: Storable Propellants Etienne Dumont, Alexander Kopp, Carina Ludwig, Nicole Garbers DLR, Space Launcher Systems Analysis (SART), Bremen, Germany [email protected] Abstract In the frame of a project funded by ESA, a consortium led Subscripts, Abbreviations by Avio in cooperation with Snecma, Cira, and DLR is ATV Automated Transfer Vehicle performing the preliminary design of a High-Thrust in- CDF Concurrent Design Facility Space Liquid Propulsion Stage for two different types of ECSS European Cooperation on Space manned missions beyond Earth orbit. For these missions, Standardization one or two 100 ton stages are to be used to propel a Elec assy electronic assembly manned vehicle. Three different propellant combinations; EPS Etage à propergols stockables (Ariane 5’s LOx/LH2, LOx/CH4 and MON-3/MMH are being storable propellant stage) compared. GNC Guidance Navigation and Control HTS High-Thrust Stage The preliminary design of the storable variant (MON- IF Interface 3/MMH) has been performed by DLR. The Aestus II ISS International Space Station engine with a large nozzle expansion ratio has been LEO Low Earth Orbit chosen as baseline. A first iteration has demonstrated, that LEOP Launch and Early Orbit Phase it indeed provides the best performance for the storable LH2 Liquid Hydrogen propellant combination, when considering all engines LOx Liquid Oxygen available today or which may be available in a short- to MLI Multi-Layer Insulation medium term.
    [Show full text]
  • Materials for Liquid Propulsion Systems
    https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost.
    [Show full text]
  • Cryogenic Technology & Rocket Engines
    ISSN (O): 2393-8609 International Journal of Aerospace and Mechanical Engineering Volume 2 – No.5, August 2015 Cryogenic Technology & Rocket Engines AKHIL GARG KARTIK JAKHU KISHAN SINGH ABHINAV B.Tech – Aerospace B.Tech – Aerospace B.Tech – Aerospace MAURYA Engg. Engg. Engg. B.Tech – Aerospace PUNJAB PUNJAB PUNJAB Engg. TECHNICAL TECHNICAL TECHNICAL PUNJAB UNIVERSITY, UNIVERSITY, UNIVERSITY, TECHNICAL JALANDHAR JALANDHAR JALANDHAR UNIVERSITY, akhilgarg.313@g kartik.lphawk@g kishansngh1996 JALANDHAR mail.com mail.com @gmail.com abhinavguru123 @gmail.com ABSTRACT 3.2 What is Cryogenic Rocket Engine? This paper is all about the rocket engine involving the use of A cryogenic rocket engine is a rocket engine that cryogenic technology at a cryogenic temperature (123K). This uses a cryogenic fuel or oxidizer, that is, its fuel or basically uses the liquid oxygen and liquid hydrogen as an oxidizer (or both) is gases liquefied and stored at oxidizer and fuel, which are very clean and non-pollutant very low temperatures. Notably, these engines were fuels compared to other hydrocarbon fuels like petrol, diesel, one of the main factors of the ultimate success in gasoline, LPG, CNG, etc., sometimes, liquid nitrogen is also reaching the Moon by the Saturn V rocket. used as an fuel. During World War II, when powerful rocket engines were first considered by the German, American and Keywords Soviet engineers independently, all discovered that Rocket engine, Cryogenic technology, Cryogenic temperature, rocket engines need high mass flow rate of both Liquid hydrogen and Oxygen. oxidizer and fuel to generate a sufficient thrust. At that time oxygen and low molecular weight 1.
    [Show full text]
  • Analysis of Regenerative Cooling in Liquid Propellant Rocket Engines
    ANALYSIS OF REGENERATIVE COOLING IN LIQUID PROPELLANT ROCKET ENGINES A THESIS SUBMITTED TO THE GRADUATE SCHOOL OF NATURAL AND APPLIED SCIENCES OF MIDDLE EAST TECHNICAL UNIVERSITY BY MUSTAFA EMRE BOYSAN IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE IN MECHANICAL ENGINEERING DECEMBER 2008 Approval of the thesis: ANALYSIS OF REGENERATIVE COOLING IN LIQUID PROPELLANT ROCKET ENGINES submitted by MUSTAFA EMRE BOYSAN ¸ in partial fulfillment of the requirements for the degree of Master of Science in Mechanical Engineering Department, Middle East Technical University by, Prof. Dr. Canan ÖZGEN Dean, Gradute School of Natural and Applied Sciences Prof. Dr. Süha ORAL Head of Department, Mechanical Engineering Assoc. Prof. Dr. Abdullah ULAŞ Supervisor, Mechanical Engineering Dept., METU Examining Committee Members: Prof. Dr. Haluk AKSEL Mechanical Engineering Dept., METU Assoc. Prof. Dr. Abdullah ULAŞ Mechanical Engineering Dept., METU Prof. Dr. Hüseyin VURAL Mechanical Engineering Dept., METU Asst. Dr. Cüneyt SERT Mechanical Engineering Dept., METU Dr. H. Tuğrul TINAZTEPE Roketsan Missiles Industries Inc. Date: 05.12.2008 I hereby declare that all information in this document has been obtained and presented in accordance with academic rules and ethical conduct. I also declare that, as required by these rules and conduct, I have fully cited and referenced all material and results that are not original to this work. Name, Last name : Mustafa Emre BOYSAN Signature : iii ABSTRACT ANALYSIS OF REGENERATIVE COOLING IN LIQUID PROPELLANT ROCKET ENGINES BOYSAN, Mustafa Emre M. Sc., Department of Mechanical Engineering Supervisor: Assoc. Prof. Dr. Abdullah ULAŞ December 2008, 82 pages High combustion temperatures and long operation durations require the use of cooling techniques in liquid propellant rocket engines.
    [Show full text]
  • 19940015753.Pdf
    National Aeronautics and Educational Product Space Administration Teachers I Grades 2-6 I Office of Education and Human Resources Education Division _o N N cO 0 u_ 0 N t_ I ,.-, CO ,4" U O" 0_ _ Z _ 0 0 tM < u Is LIJ I-. _-.q4" W_ O ul ,,_ W;Z. INWel I I,,-. UJ .... 0,. i,-,{ .... u4 uJ I-,- .. IU_ Z_ .1 i ! I i I j | ] ROCKETS Physical Science Teacher's Guide with Activities National Aeronautics and Space Administration Office of Human Resources and Education Education Division This publication is in the Public Domain and is not protected by copyright. Permission is not required for duplication. EP-291 July 1993 Acknowledgments This publication was developed for the National Aeronautics and Space Administra- tion with the assistance of the many educa- tors of the Aerospace Education Services Program, Oklahoma State University. Writer: Gregory L. Vogt, Ed.D. Teaching From Space Program NASA Johnson Space Center Houston, TX Editor: Carla R. Rosenberg Teaching From Space Program NASA Headquarters Washington, DC Table of Contents How To Use This Guide ............................... 1 Activities and Demonstration Matrix ............. 2 Brief History of Rockets ................................ 3 Rocket Principles ......................................... 8 Practical Rocketry ...................................... 12 Activities and Demonstrations .................... 19 Glossary ..................................................... 40 NASA Educational Materials And Suggested Readings .......................... 41 NASA Educational Resources ................... 42 Evaluation Card ..................................... Insert ii How To Use This Guide vehiclesockets arein theexistence.oldest formEarlyofrocketsself-containedwere in use more than two thousand years ago. Over a long and exciting history, rockets have evolved from simple tubes filled with black powder into mighty vehicles capable of launching a spacecraft out into the galaxy.
    [Show full text]
  • First Stage of a Highly Reliable Reusable Launch System
    First Stage of a Highly Reliable Reusable Launch System * $ Kurt J. Kloesel , Jonathan B. Pickrelf, and Emily L. Sayles NASA Dryden Flight Research Center, Edwards, California, 93523-0273 Michael Wright § NASA Goddard Space Flight Center, Greenbelt, Maryland, 20771-0001 Darin Marriott** Embry-Riddle University, Prescott, Arizona, 86301-3720 Dr. Leo Hollandtf General Atomics Electromagnetic Systems Division, San Diego, California, 92121-1194 Dr. Stephen Kuznetsov$$ Power Superconductor Applications Corporation, New Castle, Pennsylvania, 16101-5241 Electromagnetic launch assist has the potential to provide a highly reliable reusable first stage to a space access system infrastructure at a lower overall cost. This paper explores the benefits of a smaller system that adds the advantages of a high specific impulse air-breathing stage and supersonic launch speeds. The method of virtual specific impulse is introduced as a tool to emphasize the gains afforded by launch assist. Analysis shows launch assist can provide a 278-s virtual specific impulse for a first-stage solid rocket. Additional trajectory analysis demonstrates that a system composed of a launch-assisted first-stage ramjet plus a bipropellant second stage can provide a 48-percent gross lift-off weight reduction versus an all-rocket system. The combination of high-speed linear induction motors and ramjets is identified, as the enabling technologies and benchtop prototypes are investigated. The high-speed response of a standard 60 Hz linear induction motor was tested with a pulse width modulated variable frequency drive to 150 Hz using a 10-lb load, achieving 150 mph. A 300-Hz stator-compensated linear induction motor was constructed and static-tested to 1900 lbf average.
    [Show full text]
  • AVAILABLE PROM Superintendent of Documents, U
    DOCUMENT MUNE ED 096 097 32 016 450 TITLE Aerospace Bibliography. Sixth Edition. INSTITUTION National Aerospace Education Cocncil, Washington, D.C. SPONS AGENCY National Aeronautics and Space Administration, Washington, D.C. REPORT NO EP-48 PUB DATE 72 NOTE 115p. AVAILABLE PROM Superintendent of Documents, U. S. Government Printing Office, Washington, D. C. 20402 (Stock No. 3300-0460, $1.25) MIS PRICE BP-$0.75 HC-$5.40 PLUS POSTAGE DESCRIPTORS *Aerospace Technology; *Annotated Bibliographies; Astronomy; *Booklists; Career Opportunities; Information Sources; *Reference Materials; Satellite Laboratories; Space Sciences IDENTIFIERS NASA; National Aeronautics and Space Administration ABSTRACT This sixth edition of the National Aeronautics and Space Administration's (NASA) bibliography presentsan updated list of books, references, periodicals, and other educational materials related to space flight and space science. To find materialson a particular subject and for a specific reading level,users are advised to refer first to Part 1-Subject Index. Detailsare found in Part 2. Part 3 includes listings of reference materials related to space flight and space science, while Part 4 provides as list of related periodicals. Elementary and secondary teachers and adult readers will find this bibliography useful. There isan index to titles, a description of NASA services, anda list of addresses of sources of books and other materials. For the most part, books listed in this bibliography bear copyright dates beginning with 1969through fall 1971. (EB) sixth edition aerospace bibliography US DEPARTMENT nF NEAL TN EDUCATION I WELFARE NATIONAL INSTITUTE OF EDUCATION IIUS00( ',MI NtIIA } Pito {) xm et r 1S 1,1 (I t)I WOY tilt Pt USON 014(.AN 11 ',ors, uk .1,.N 111 itit,I PO,NtS Of v t., OW (11,N.ON% ST DO NOT NI (I csA14.
    [Show full text]
  • Space in Space
    SPACE IN SPACE Michal V{J~ÁK 16.5.2019 1. AREA IN SPACE OPPORTUNITY 2. WHY IS IT STILL HERE ? 3. WHAT IS IN PROGRESS ? Technologie které známe, máme a ovládáme 4. WHAT IS THE FUTURE ? musíme umět spojit do komplexních celků tady 5. HOW CAN WE MANAGE IT ? v Česku a tyto pak obchodovat. 6. VEGA EXAMPLE Jedině tak se dostaneme na vyšší příčky 7. EPD EXAMPLE hodnotových řetězců. 8. VISION Je třeba spolupracovat a důvěřovat si. Michal Vajdák Mezi občany nesmějí platit jiné privileje, diplomy a erby, než které spočívají v zásluhách, práci a rozumu. (krédo bratří Grégrů na pamětní desce při vstupu do pražského Žofína) AREA IN SPACE OPPORTUNITY Space Business . Higher levels of value chains opportunity . Space - the technology development driver . No boundaries in expansion . Space - the unique integrator of human activities . Research activities to explore NEW . Development of new technologies . Commercialization of new technologies . A new age of autonomous systems and businesses . UP and DOWN stream of technology transfer WHY IS IT STILL HERE ? Business Specifics . Low volume production . National interests and limitations . New technologies maturation needs . Significant SME support . Need for autonomous systems WHAT IS IN PROGRESS = ALREADY GONE Space Areas . Low Earth orbit satellites . Defense on orbit . Stratospheric applications . Mission spacecraft . Launchers under development (VEGA-C/E, Ariane 6/7) Source: ESA WHAT IS THE FUTURE ? Future Space Areas . New launcher technologies . Human flight technologies as space safety and security, transportation of humans and cargo or sub-orbital spaceflights . Spacecraft technologies to be used for a variety of purposes, including deep space missions (e.g.
    [Show full text]
  • Worldwide Equipment Guide
    WORLDWIDE EQUIPMENT GUIDE TRADOC DCSINT Threat Support Directorate DISTRIBUTION RESTRICTION: Approved for public release; distribution unlimited. Worldwide Equipment Guide Sep 2001 TABLE OF CONTENTS Page Page Memorandum, 24 Sep 2001 ...................................... *i V-150................................................................. 2-12 Introduction ............................................................ *vii VTT-323 ......................................................... 2-12.1 Table: Units of Measure........................................... ix WZ 551........................................................... 2-12.2 Errata Notes................................................................ x YW 531A/531C/Type 63 Vehicle Series........... 2-13 Supplement Page Changes.................................... *xiii YW 531H/Type 85 Vehicle Series ................... 2-14 1. INFANTRY WEAPONS ................................... 1-1 Infantry Fighting Vehicles AMX-10P IFV................................................... 2-15 Small Arms BMD-1 Airborne Fighting Vehicle.................... 2-17 AK-74 5.45-mm Assault Rifle ............................. 1-3 BMD-3 Airborne Fighting Vehicle.................... 2-19 RPK-74 5.45-mm Light Machinegun................... 1-4 BMP-1 IFV..................................................... 2-20.1 AK-47 7.62-mm Assault Rifle .......................... 1-4.1 BMP-1P IFV...................................................... 2-21 Sniper Rifles.....................................................
    [Show full text]