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On Orbital Debris JEFF FOUST, COLLEGE PARK, Md
NOVEMBER 24, 2014 SPOTLIGHT Clyde Space See page 12 www.spacenews.com VOLUME 25 ISSUE 46 $4.95 ($7.50 Non-U.S.) PROFILE/22> YVONNE PENDLETON DIRECTOR, SOLAR SYSTEM EXPLORATION RESEARCH VIRTUAL INSTITUTE INSIDE THIS ISSUE LAUNCH INDUSTRY Swift Development of Ariane 6 Urged Applauding the end of a French-German impasse over the Ariane 6 rocket, the European Satellite Operators Association said the vehicle needs to be in service as quickly as possible. See story, page 8 ATK Hints at Antares Engine Selection Alliant Techsystems Chief Executive Mark DeYoung said there are no near-term liquid- propulsion alternatives to Russian engines for U.S. rockets. See story, page 6 ESA PHOTO Virginia May Seek Federal Funds for Wallops > “We have found a compromise that is OK for both countries, for the other participating states and also for industry,” Brigitte Zypries (above), Germany’s Virginia’s two U.S. senators said they may seek federal funds to cover $20 million in repairs to the space minister, said of an agreement under which Germany and France will back the Ariane 6 rocket and scrap the Ariane 5 Midlife Evolution. Wallops Island launch pad damaged when Orbital Sciences’ Antares exploded. See story, page 6 MILITARY SPACE Protected Tactical Waveform Taking Shape German-French Compromise The U.S. Air Force is expected to demonstrate its protected tactical waveform in new modems and reworked terminals as early as 2018. See story, page 11 U.S. To Grant Indirect Access to Space Fence Paves Direct Path to Ariane 6 The Pentagon’s international space surveillance partners will have indirect access to data from the Air Force’s next-generation Space Fence tracking system. -
MT Aerospace (Germany)
https://ntrs.nasa.gov/search.jsp?R=20080014278 2019-08-30T04:19:50+00:00Z European Directions for Hypersonic Thermal Protection Systems and Hot Structures 31st Annual Conference on Composites Materials and Structures Daytona Beach, FL January 22, 2007 David E. Glass NASA Langley Research Center, Hampton, VA 23681 Approved for Public Release, Distribution Unlimited Agenda ♦ Background • Comments on prior ESA workshop • X-38 • Hopper ♦ Flight Vehicle Based Technology Development • IXV (ESA) • EXPERT (ESA) • USV (Italy) • SHEFEX (Germany) • SHyFE (UK) • LEA (France) • Foton (Russia) ♦ Non-Vehicle Specific Technology ♦ Concluding Remarks 2 European TPS and Hot Structures Research and Development ♦TPS and hot structures research and development critical for future space vehicles ♦Developing next generation TPS and hot structures technology (not Space Shuttle derived technology) ♦Long-term funding based on technology needs ♦Wide industry support and commitment to X-38 program ♦Test facilities developed for TPS and hot structures development • Thermal/structural test chamber • Arc-jet tunnels developed in recent years ♦Technology development has broad base • Fabrication • Testing • Large components • Fasteners • Bearings • Oxidation protection • Damage repair • Life cycle Wayne Sawyer comments from previous ESA TPS & Hot Structures Workshop 3 European TPS and Hot Structures Research and Development ♦ Proposing numerous experimental launch vehicles dedicated to or with TPS and hot structures research of prime consideration ♦ Committing significant -
Mission Analysis and Preliminary Re-Entry Trajectory Design of the DLR Reusability Flight Experiment Refex
8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Mission Analysis and Preliminary Re-entry Trajectory Design of the DLR Reusability Flight Experiment ReFEx Sven Stappert*, Peter Rickmers*, Waldemar Bauer*, Martin Sippel* *German Aerospace Center (DLR), Institute of Space Systems, Robert-Hooke-Straße 7, 28359 Bremen [email protected], [email protected], [email protected], [email protected] Abstract Driven by the recently increased demand for investigating reusable launchers, the German Aerospace Center (DLR) is currently developing the Reusability Flight Experiment (ReFEx). The goal is to demonstrate the capability of performing an atmospheric re-entry, representative of a possible future winged reusable stage, and to develop and test key technologies for such reusable stages. The flight demonstrator ReFEx shall perform a controlled and autonomous re-entry from hypersonic velocity of approximately Mach 5 down to subsonic velocity after separation from the VSB-30 booster. The focus of this paper is the re-entry trajectory design for the ReFEx mission. Abbreviations AoA Angle of Attack AVS Avionics BC Ballistic Coefficient BoGC Begin of Guided Control CALLISTO Cooperative Action Leading to Launcher Innovation in Stage Tossback Operation DOF Degree of Freedom ELV Expendable Launch Vehicle EoE End Of Experiment GNC Guidance, Navigation and Control L/D Lift-to-Drag Ratio FPA Flight Path Angle LFBB Liquid Fly-Back Booster MECO Main Engine Cut-Off RCS Reaction Control System RLV Reusable Launch Vehicle TOSCA Trajectory Optimization and Simulation of Conventional and Advanced Spacecraft VTHL Vertical Takeoff, Horizontal Landing VTVL Vertical Takeoff, Vertical Landing 1. Introduction The recent successes of the emerging private space companies SpaceX and Blue Origin in landing, recovering and relaunching reusable first stages have demonstrated the possibility of building reliable and competitive reusable first stages. -
L. Summerera,∗, A. Galvezb, D. Izzoa, F
64nd International Astronautical Congress, Beijing, China. Copyright 2013 by ESA. Published by the IAF, with permission and released to the IAF to publish in all forms. IAC-13.E.6.1.6 COMPETITIONS, GAMES AND PRIZES - MEANS FOR ADVANCED SPACE RESEARCH? L. Summerera,∗, A. Galvezb, D. Izzoa, F. Salzgeberc, A. de Clercqc, P. Manesc aESA Advanced Concepts Team, Keplerlaan 1, 2201 Noordwijk, The Netherlands bESA General Studies Programme, rue Mario Nikis, 75015 Paris, France cESA Technology Transfer Programme, Keplerlaan 1, 2201 Noordwijk, The Netherlands Abstract The traditional main mechanisms to advance science and technology in the space sector have recently been complemented by the use of competitions, prizes and games. Historically competitions and ex-ante prizes have played an important role among the tools of governments to stimulate innovation and advance science and technologies. Triggered by the success of the Ansari X-Prize in late 1990s / early 2000, these mechanisms have steadily gained grounds and supporters, also among governments. Scholarly literature on the effectiveness, advantages and disadvantages of these methods is emerging but still scarce. Most of the available scholarly literature assesses their impact based on US case studies and examples. The present paper provides a first analysis of these mechanisms and tools within the European Space Agency (ESA), based on three different areas: scientific research within its Advanced Concepts Team, business and innovation oriented competitions and prizes within the technology transfer programme and system level studies within the General Studies Programme. The ESA Advanced Concepts Team has experimented and used new ways of engaging with the larger scientific community via the use of scientific competitions, online games and scientific crowdsourcing experiments. -
Jacques Tiziou Space Collection
Jacques Tiziou Space Collection Isaac Middleton and Melissa A. N. Keiser 2019 National Air and Space Museum Archives 14390 Air & Space Museum Parkway Chantilly, VA 20151 [email protected] https://airandspace.si.edu/archives Table of Contents Collection Overview ........................................................................................................ 1 Administrative Information .............................................................................................. 1 Biographical / Historical.................................................................................................... 1 Scope and Contents........................................................................................................ 2 Arrangement..................................................................................................................... 2 Names and Subjects ...................................................................................................... 2 Container Listing ............................................................................................................. 4 Series : Files, (bulk 1960-2011)............................................................................... 4 Series : Photography, (bulk 1960-2011)................................................................. 25 Jacques Tiziou Space Collection NASM.2018.0078 Collection Overview Repository: National Air and Space Museum Archives Title: Jacques Tiziou Space Collection Identifier: NASM.2018.0078 Date: (bulk 1960s through -
Electric Propulsion: a Key Enabling Technology for Planetary Exploration*
Electric Propulsion: A Key Enabling Technology for Planetary Exploration* A White Paper for the Planetary Science and Astrobiology Decadal Survey 2023-2032 Jay Polk, Jet Propulsion Laboratory, California Institute of Technology [email protected], 818-281-1094 George Soulas, NASA Glenn Research Center [email protected], 216-977-7419 Andy Hoskins, Aerojet Rocketdyne [email protected], 425-945-6362 *The information presented in this white paper about future mission concepts and power systems is pre- decisional and is provided for planning and discussion purpose only. A portion of this work was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration (80NM0018D0004). 1 Abstract. Electric propulsion is now widely accepted by industry, with over 900 operational spacecraft using electric thrusters as of June 30, 2020. Electric propulsion provides dramatic reductions in propellant mass which can enable many demanding mission concepts to meet their scientific and operational goals. It has already proven to be a critical enabling technology on science missions such as Dawn, Hayabusa I and II, and BepiColombo and is the key to making missions in development like Psyche and a potential Mars Sample Return possible. These examples show that electric propulsion can enable the use of smaller launch vehicles, provide mass margins that make missions much more robust, yield much greater flexibility in launch dates, reduce the number of critical events, and, in some cases, reduce trip times by eliminating the need for gravity assists. Electric propulsion systems developed by industry for commercial spacecraft and NASA- developed technologies for higher power and specific impulse support current mission applications, but ensuring that electric propulsion can meet the demands of future missions requires continued investment by NASA. -
Multidisciplinary Design Optimization of Launch Vehicles Mathieu Balesdent
Multidisciplinary Design Optimization of Launch Vehicles Mathieu Balesdent To cite this version: Mathieu Balesdent. Multidisciplinary Design Optimization of Launch Vehicles. Optimization and Control [math.OC]. Ecole Centrale de Nantes (ECN), 2011. English. tel-00659362 HAL Id: tel-00659362 https://tel.archives-ouvertes.fr/tel-00659362 Submitted on 12 Jan 2012 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. ÉCOLE DOCTORALE SCIENCES POUR L’INGÉNIEUR, GÉOSCIENCES, ARCHITECTURE École Centrale de Nantes Année 2011 Thèse de Doctorat Spécialité : Génie Mécanique présentée et soutenue publiquement par Mathieu BALESDENT le 3 novembre 2011 à l’Office National d’Etudes et de Recherches Aérospatiales OPTIMISATION MULTIDISCIPLINAIRE DE LANCEURS (Multidisciplinary Design Optimization of Launch Vehicles) JURY Président : Jean-Antoine Désidéri Directeur de Recherche, INRIA Rapporteurs : David Bassir Docteur, HDR, Université de Technologie de Belfort-Montbéliard Attaché pour la Science et la Technologie, Ministère des Affaires Etrangères Patrick Siarry Professeur, Université Paris-Est Créteil Val-de-Marne Examinateurs : Philippe Dépincé Professeur, Ecole Centrale de Nantes Michèle Lavagna Associate Professor, Politecnico di Milano Rodolphe Le Riche Docteur, HDR, CNRS - Ecole des Mines de Saint-Etienne Invités : Nicolas Bérend Ingénieur, Onera Julien Laurent-Varin Docteur, CNES Directeur de thèse : Philippe DÉPINCÉ Encadrant Onera : Nicolas BÉREND Laboratoires : Office National d’Etudes et de Recherches Aérospatiales Institut de Recherche en Communications et Cybernétique de Nantes N◦ E.D. -
1 the Lifecycle of Hollows on Mercury
The Lifecycle of Hollows on Mercury: An Evaluation of Candidate Volatile Phases and a Novel Model of Formation. 1 1 2 3 M. S. Phillips , J. E. Moersch , C. E. Viviano , J. P. Emery 1Department of Earth and Planetary Sciences, University of Tennessee, Knoxville 2Planetary Exploration Group, Johns Hopkins University Applied Physics Laboratory 3Department of Astronomy and Planetary Sciences, Northern Arizona University Corresponding author: Michael Phillips ([email protected]) Keywords: Mercury, hollows, thermal model, fumarole. Abstract On Mercury, high-reflectance, flat-floored depressions called hollows are observed nearly globally within low-reflectance material, one of Mercury’s major color units. Hollows are thought to be young, or even currently active, features that form via sublimation, or a “sublimation-like” process. The apparent abundance of sulfides within LRM combined with spectral detections of sulfides associated with hollows suggests that sulfides may be the phase responsible for hollow formation. Despite the association of sulfides with hollows, it is still not clear whether sulfides are the hollow-forming phase. To better understand which phase(s) might be responsible for hollow formation, we calculated sublimation rates for 57 candidate hollow-forming volatile phases from the surface of Mercury and as a function of depth beneath regolith lag deposits of various thicknesses. We found that stearic acid (C18H36O2), fullerenes (C60, C70), and elemental sulfur (S) have the appropriate thermophysical properties to explain hollow formation. Stearic acid and fullerenes are implausible hollow-forming phases because they are unlikely to have been delivered to or generated on Mercury in high enough volume to account for hollows. -
After Neptune Odyssey Design
Concept Study Team We are enormously proud to be part of a large national and international team many of whom have contributed their time in order to make this study a very enjoyable and productive experience. Advancing science despite the lockdown. Team Member Role Home Institution Team Member Role Home Institution Abigail Rymer Principal Investigator APL George Hospodarsky Plasma Wave Expert U. of Iowa Kirby Runyon Project Scientist APL H. Todd Smith Magnetospheric Science APL Brenda Clyde Lead Engineer APL Hannah Wakeford Exoplanets U. of Bristol, UK Susan Ensor Project Manager APL Imke de Pater Neptune expert Berkeley Clint Apland Spacecraft Engineer APL Jack Hunt GNC Engineer APL Jonathan Bruzzi Probe Engineer APL Jacob Wilkes RF Engineer APL Janet Vertisi Sociologist, teaming expert Princeton James Roberts Geophysicist APL Kenneth Hansen NASA HQ Representative NASA HQ Jay Feldman Probe Engineer NASA Ames Krista Soderlund Neptune WG Co-lead U. of Texas Jeremy Rehm Outreach APL Kunio Sayanagi Neptune WG Co-lead Hampton U. Jorge Nunez Payload Manager APL Alan Stern Triton WG Co-lead SwRI Joseph Williams Probe Engineer NASA Ames Lynne Quick Triton WG Co-lead GSFC Juan Arrieta Tour Design NablaZero lab Tracy Becker Icies and Rings WG Co-lead SwRI Kathleen Mandt Triton Science APL Matthew Hedman Icies and Rings WG Co-lead U. of Idaho Kelvin Murray Schedule APL Ian Cohen Aurora/Mag WG Co-lead APL Kevin Stevenson Exoplanets APL Frank Crary Aurora/Mag WG Co-lead U. of Colorado Kurt Gantz Mechanical Design Engineer APL Jonathan Fortney Exoplanets WG Lead UCSC Larry Wolfarth Cost Analysis APL Adam Masters Magnetospheric Science Imperial College Leigh Fletcher Physicist U. -
A Survey of Automatic Control Methods for Liquid-Propellant Rocket Engines
A survey of automatic control methods for liquid-propellant rocket engines Sergio Pérez-Roca, Julien Marzat, Hélène Piet-Lahanier, Nicolas Langlois, Francois Farago, Marco Galeotta, Serge Le Gonidec To cite this version: Sergio Pérez-Roca, Julien Marzat, Hélène Piet-Lahanier, Nicolas Langlois, Francois Farago, et al.. A survey of automatic control methods for liquid-propellant rocket engines. Progress in Aerospace Sciences, Elsevier, 2019, pp.1-22. 10.1016/j.paerosci.2019.03.002. hal-02097829 HAL Id: hal-02097829 https://hal.archives-ouvertes.fr/hal-02097829 Submitted on 12 Apr 2019 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. A survey of automatic control methods for liquid-propellant rocket engines Sergio Perez-Roca´ a,c,∗, Julien Marzata,Hel´ ene` Piet-Lahaniera, Nicolas Langloisb, Franc¸ois Faragoc, Marco Galeottac, Serge Le Gonidecd aDTIS, ONERA, Universit´eParis-Saclay, Chemin de la Huniere, 91123 Palaiseau, France bNormandie Universit´e,UNIROUEN, ESIGELEC, IRSEEM, Rouen, France cCNES - Direction des Lanceurs, 52 Rue Jacques Hillairet, 75612 Paris, France dArianeGroup SAS, Forˆetde Vernon, 27208 Vernon, France Abstract The main purpose of this survey paper is to review the field of convergence between the liquid-propellant rocket- propulsion and automatic-control disciplines. -
Marcopolo-R Near Earth Asteroid Sample Return Mission
1 MarcoPolo-R Near Earth Asteroid Sample Return Mission Proposal Core Members Europe Maria Antonietta Barucci LESIA – Paris Observatory, F [email protected] (Lead Proposer) Patrick Michel Univ. Nice, CNRS, OCA, F [email protected] (Co-Lead Proposer) Philip A. Bland Imperial College, London, UK [email protected] Hermann Böhnhardt MPS, Katlenburg-Lindau, D [email protected] John R. Brucato INAF – Obs. of Arcetri, I [email protected] Adriano Campo Bagatin Univ. Alicante, E [email protected] Priscilla Cerroni INAF – IASF, Roma, I [email protected] Elisabetta Dotto INAF – Obs. of Roma, I [email protected] Alan Fitzsimmons QUB, Belfast, UK [email protected] Ian A. Franchi Open Univ., Milton Keynes, UK [email protected] Simon F. Green Open Univ., Milton Keynes, UK [email protected] Luisa-M. Lara IAA – CSIC, Granada, E [email protected] Javier Licandro IAC-CSIC, Tenerife, E [email protected] Bernard Marty CRPG, Nancy, F [email protected] Karri Muinonen Univ. Helsinki and FGI, FIN [email protected] Andres Nathues MPS, Katlenburg-Lindau, D [email protected] Jürgen Oberst DLR Berlin, D [email protected] François Robert MNHN, Paris, F [email protected] Raffaele Saladino Univ. of Tuscia, Viterbo, I [email protected] Josep M. Trigo-Rodriguez CSIC – IEEC, Barcelona, E [email protected] Stephan Ulamec DLR RB – MC, Cologne, D [email protected] USA Andrew Cheng JHU – APL, Maryland [email protected] (Lead U.S. Collaborator) Lance Benner JPL, California [email protected] Richard P. -
2013 Annual Report
Annual Report Year Ended December 31, 2013 September 18, 2014 Dear EchoStar Corporation Shareholders, In 2013, we made tremendous progress and, yet again, proved why we are a leader in the satellite and telecommunications industry. Our unique combination of knowledge and experience from end-to-end satellite operations, video delivery and broadcast technologies, and data networks allows us to deliver a unique and impressive suite of products and services to support our continued success. EchoStar ended the 2013 fiscal year with a solid performance. Our total revenue was $3.3 billion compared to $3.1 billion in 2012, representing a 6.7% increase. EBITDA was $650 million in 2013, compared to $794 million in 2012, and included $139 million higher investment gains and $46 million in dividends that were not repeated in 2013. We ended the year with $1.6 billion in cash and marketable securities, which gives us the resources necessary to pursue strategic opportunities to position ourselves for global growth. We continue to deliver on our commitments to customers, partners, employees, and shareholders. EchoStar had a stellar 2013 performance partially due to the continued success of the Hopper whole-home DVR product line, including the launch of the award-winning Hopper with Sling. In addition, we achieved record numbers in growth for our HughesNet subscribers, which totaled more than 800,000 by the end of 2013. Hughes broadened its suite of services by launching HughesNet Voice, an integrated VoIP option, that rivals the triple play offered by competitors. In December 2013, we acquired Solaris Mobile, a company based in Ireland and licensed by the European Union, to provide mobile satellite services and complementary ground component services covering the entire European Union.