Sixth European Space Mechanisms & Tribology Symposium

Total Page:16

File Type:pdf, Size:1020Kb

Sixth European Space Mechanisms & Tribology Symposium SUB Gattlngen 206 766 580 esa SP-374 August 1995 Sixth European Space Mechanisms & Tribology Symposium An international symposium organised by the European space Agency and the Swiss Space Industries and held at the Technopark, Zurich, Switzerland on 4-6 October 1995 european space agency / agence spatiale europeenne 8-10, rue Mario-Nikis, 75738 PARIS CEDEX, France CONTENTS Opening Session La lubrification de la montre mecanique xi P.E. Debely, Association Suisse pour la Recherche Horlogere, NeucMtel, CH Future directions in miniature spacecraft and microelectromechanical systems (no paper received) C.A. Kukkonen, Jet Propulsion Laboratory, USA Session 1: Pointing and Scanning Mechanisms (I) IASI Instrument: Development of the Scan Subsystem 1 M. Lavadoux, Sag em, F M. Privat, CNES, Toulouse, F V. Artinian, AVCON, Agoura Hills, CA, USA High-precision pointing device for the LASCO instrument on SOHO 9 F. Burger & J. Eder, Kayser-Th rede, D Gome scan mechanism 15 M. Fibbi, F. Fabbrizzi & M. Galanti, Officine Galileo, I G. Harvey, R.A. Rowntree & B.J. Williams, ESTL, Risley, Uk Long-life, elevated-velocity slip-ring contacts investigation 21 P.A. Mciusli & A. Gisiger, Mecanex, Nyon, CH J.M. Gavira, ESTEC, Noordwijk, NL Session 2: Tribology (I) MoSx, a solid lubricant: yes, but which scales of tribological interpretation should be used? The consequences on the friction of mechanisms 29 S. Decartes, M. Cassard & Y. Berthier, INSA, Villeurbanne, F A. Ginet & A. Aubert, CES/CEREM, Grenoble, F A practical assessment of data repeatability and reproducibility in tribometer tests for space applications 35 J.M. Cunningham, ESTL, Risley, UK C. Garcia Marirrodriga, ESTEC, Noordwijk, NL Friction energy loss in annular ball bearings oscillations. 45 A. Borrien, E. Conde & J. Sicre, CNES, Toulouse, F Adhesion of materials by impact contacts in vacuum ., 431 M. Maillat, H. Boving, M. De Muynck & P, Voumard, CSEM, Neuchatel, CH HE. Hintermann, University of Neuchatel, Neuchatel, CH Contacting plane contact: selection of material pairs with high friction coefficient 51 - M. Durand, Aerospatiale, Cannes-la-Bocca, F IV Session 3: Deployment Mechanisms Four-bar linkage as optimization of a spring-driven deployment mechanism for Polar Platform DRS antenna mechanisms 59 /./. Bueno & Y. Gutierrez, Sener, Las Arenas, E The qualification test programme of the ENVISAT solar array mechanism 65 R. Zwanenburg, Fokker, Leiden, NL Development of mechanism to extend the solar-array paddle for ADEOS 73 A. Tanaka, T. Kawamura & K. Matsumura, Toshiba Co., Kawasaki, J R. Kuramasu, K. Inoue & I. Kanazawa, NASDA, Tokyo, J Session 4: Scientific Instrument Mechanisms High-performance pointing and scanning mechanisms for ATLID and SPOT 5 81 T. Blais & J.P. Hermier, MMS, Toulouse, F Kinematic six-ball guide for long-stroke optical delay line 91 B.C. Braam, HA. van Mierlo & B. Snijders, TNO/TPD, Delft, NL Development of an actuator for CAPS instrument on spacecraft Cassini 97 7". Ylikorpi, T. luntama, K. Viherkanto, V.-P. Lappalainen, H. Hannula & H. Huomo, VTT, SF Mechanization of the fine-guidance sensors of the Hubble Space Telescope 103 J.F. Vollaro, Hughes, Danbury, CT, USA Mechanisms for atmospheric research by spaceborne LIDAR techniques 425 H. Heimel & E. Hettlage, Teldix, Heidelberg, D Session 5: Special Functions Huygens separation mechanisms Ill U. Herlach, P. Tatalias, B. Schmkl & D. Mussett, Oerlikon-Contraves, Zurich, CH TMM & M tether deployment mechanism features and test results 119 R. Licata, Alenia Spazio, Turin, I J.M. Gavira, ESTEC, Noordwijk, NL The development of an ion thruster alignment mechanism (ITAM) for ARTEMIS 137 M. Falkner & C. Schwarzinger, ORS, Vienna, A Design and development of band-separation joint for the horizontal separation system of the polar satellite launch vehicle (India) heatshield 149 E.J. Francis, S. Unnikrishnan Nair, J. Maran, S.V. Shenoi & M.K.A. Majeed, Vikram SarabhaiSpace Center, IN ESA mechanisms requirements 157 G. Labruyere & P. Urmston, ESTEC, Noordwijk, NL Session 6: Tribology (II) New considerations on fluid lubricants for spacecraft applications 169 /. Sicre, CNES, Toulouse, F Ph. Vergne & Ph. Prat, CNRS, Lyon, F M. Pochard, Sodern, Limeil Brevannes, F Recent experience with synthetic hydrocarbon lubricants for spacecraft applications 177 D.J. Carre, C,G. Kalogeras, S.V. Didziulis, P.D. Fleischauer & R. Bauer, The Aerospace Corp., Los Angeles, CA, USA Noise analysis of dry lubricated ball bearings for a scanning Earth sensor mechanism 185 L. Nicollet & M. pochard, Sodem, Limeil Brevannes, F J. Sicre, CNES, Toulouse, F Session 7: Post-flight Investigations Post-flight investigations of the EURECA mechanisms: first results and conclusions 195 U. Kugel & M. Verain, ESTEC, Noordwijk, NL F.M. Zdrraga, GAMESA, Vitoria, E A post-flight tribological assessment of the Hubble Space Telescope solar array mechanisms 203 M.J. Anderson & K. Parker, ESTL, Risley, UK M. Eiden, ESTEC, Noordwijk, NL EURECA solar array mechanism proven performance (no paper received) R. Sebek, Fokker, NL Session 8: Actuators & Drives Gear box for space robots 213 K.J. van Brink & C. Cars tens, Stork Product Engineering, Amsterdam, NL Space mechanism actuated by a shape memory alloy component 221 G. Luciano, Aerospatiale, Cannes-la-Bocca, F G. Galet, CNES, Toulouse, F Voice-coil actuators in space 227 N. Wavre & X. Thouvenin, ETEL, Motiers, CH Session 9: Pointing and Scanning Mechanisms (II) SILEX mechanisms: which lessons after qualification? 235 F. Di Gesu & A. Brunschvig, Matra Marconi Space, Toulouse, F Design of the MIPAS-ESU mechanism 245 B. Wood, Oerlikon-Contraves, Zurich, CH VI Session 9: Pointing and Scanning Mechanisms (II) (continued) Design and performances of a rotary actuator for space applications 251 P. Juriens, ETEL, Motiers, CH G. Labruyere & M. Verain, ESTEC, Noordwijk, NL Poster Session 1: Tribology Solid-lubricant studies in high vacuum 259 C. Donnet, T. Le Mogne, M. Belin & J.M. Martin, Ecole Centrale de Lyon, Ecully, F Qualification of a new molybdenum sulfide coating 265 J. Sicre, CNES, Toulouse, F A. Aubert & A. Ginet, CEA/CEREM, Grenoble, F Y. Berthier, INSA de Lyon, Villeurbanne, F Advances in molybdenum disulphide film technology for space applications 273 E.W. Roberts & W.B. Price, ESTL, Risley, GB Interim results from ESTL studies on static adhesion and the performance of Pennzane SHF X-2000 in ball bearings 279 S. Gill & R.A. Rowntree, ESTL, Risley, GB Space-flight experience and life test performance of a synthetic hydrocarbon lubricant 285 B. Bialke, ITHACO, Ithaca, NY, USA Study on adhesion/cold welding under cyclic load and high vacuum 293 A. Merstallinger & E. Semerad, Austrian Research Centre, Seiberdorf, A B.D. Dunn, ESTEC, Noordwijk, NL H. Stori, Institut f. allgemeine Physik, Vienna, A Evaluation of dry gear lubricants for high-cycle space applications 299 H. Zhao, S.K. Chang, I. Armitage & J. Antoniazzi, Spar Aerospace Ltd., Brampton, ON, CDN Poster Session 2: Special Functions Biopan - a multi-purpose exposure facility for space research 313 F. Burger, Kayser-Threde, Munich, D Design and analysis of dcployable modular structures for a large space antenna 319 A. Meguro & J. Mitsugi, NTT Wireless systems Laboratories, Kanagawa, J End effector for on-orbit robotic servicing of payloads 325 B. C. Braam & R. Ramaker, TNO/TPD, Delft, NL An automatic bolt/nut-type latching system : 331 J.J. Gonzdlez-Vallejo & J. Arino, Sener, E Vll Poster Session 3: Sensors, Actuators and Drives High-performance stepper motors for space mechanisms 341 P. Sega, SAG EM, Paris, F Electro-mechanical mechanisms for remote actuation requirements 349 C. Courtney, L. McCormick, T. Moran & R. Stephenson, G.&H. Technology Inc., Camarillo, CA, USA Design and development of a brushless DC motor for a magnetically suspended reaction wheel (no paper received) P.M. Krishna, ISRO, IND Development of a 'smart' electric motor 355 E. Favre & J.-L. Schaer, ETEL, Motiers, CH M. Verain, ESTEC, Noordwijk, NL Life test experience on a harmonic-drive-based actuator 363 H. Heimerdinger & M. Schmid, Domier GmbH, Friedrichshafen, D Tests of a low-noise electric motor \ 369 E. Favre, M. Correvon & J.-M. Mozzon, ETEL, Motiers, CH M. Verain, ESTEC, Noordwijk, NL Encoders for space applications (no paper received) D. Gaumet, Codechamp, F Poster Session 4: Scanning and Pointing Mechanisms A precision refocusing mechanism for very low temperatures 377 J.I. Bueno, Sener, Las Arenas, E Design, development and qualification of a lightweight antenna-pointing mechanism (no paper received) M. Shmulevitz, IAI MBT, IR Mechanism qualification for SOHO SUMER 383 H. Hartwig, W. Engelhardt & R. Schmidt, Max-Planck Institut f. Aeronomie, Katlenburg-Lindau, D A prototype scan mechanism for the composite infrared spectrometer (CIRS) of the NASA/ESA Cassini mission 385 G. Michel & R. Courtin, Observatoire de Paris, Meudon, F Poster Session 5: Simulation and Tools Cabaret - a new software tool for analysis of solid-lubricated ball bearings in space applications 393 S.D. Lewis, ESTL, Risley, GB Estimation of friction torque in solid-lubricated ball bearings 401 E. Legrand, GLCS, Montreuil s. Bois, F J.—B. Mondier, CNES, Toulouse, F Vlll Poster Session 5: Simulation and Tools (continued) Software for the simulation of mechanisms 407 C. Choinkowski, Artec Aerospace, Toulouse, F J.B. Mondier, CNES, Toulouse, F Integrating motion simulation with design for space stepper motor applications 413 D.B. Marks, Honeywell Electro components, Durham, NC, USA Numerical simulation of space mechanisms - LISA separation analysis 419 M. Yorck, ESTEC, Noordwijk, NL.
Recommended publications
  • Gnc 2021 Abstract Book
    GNC 2021 ABSTRACT BOOK Contents GNC Posters ................................................................................................................................................... 7 Poster 01: A Software Defined Radio Galileo and GPS SW receiver for real-time on-board Navigation for space missions ................................................................................................................................................. 7 Poster 02: JUICE Navigation camera design .................................................................................................... 9 Poster 03: PRESENTATION AND PERFORMANCES OF MULTI-CONSTELLATION GNSS ORBITAL NAVIGATION LIBRARY BOLERO ........................................................................................................................................... 10 Poster 05: EROSS Project - GNC architecture design for autonomous robotic On-Orbit Servicing .............. 12 Poster 06: Performance assessment of a multispectral sensor for relative navigation ............................... 14 Poster 07: Validation of Astrix 1090A IMU for interplanetary and landing missions ................................... 16 Poster 08: High Performance Control System Architecture with an Output Regulation Theory-based Controller and Two-Stage Optimal Observer for the Fine Pointing of Large Scientific Satellites ................. 18 Poster 09: Development of High-Precision GPSR Applicable to GEO and GTO-to-GEO Transfer ................. 20 Poster 10: P4COM: ESA Pointing Error Engineering
    [Show full text]
  • Real-Time On-Orbit Calibration of Angles Between Star Sensor and Earth Observation Camera for Optical Surveying and Mapping Satellites
    ISPRS Annals of the Photogrammetry, Remote Sensing and Spatial Information Sciences, Volume IV-2/W5, 2019 ISPRS Geospatial Week 2019, 10–14 June 2019, Enschede, The Netherlands REAL-TIME ON-ORBIT CALIBRATION OF ANGLES BETWEEN STAR SENSOR AND EARTH OBSERVATION CAMERA FOR OPTICAL SURVEYING AND MAPPING SATELLITES Wei Liu 1*, Hui Wang 2, Weijiao Jiang 2, Fangming Qian 3, Leiming Zhu 4 1 Xi’an Research Institute of Surveying and Mapping, No.1 Middle Yanta Road, Xi’an, China - [email protected] 2 State Key Laboratory of Integrated Service Network, Xidian University, Xi’an, China - [email protected] 2 State Key Laboratory of Integrated Service Network, Xidian University, Xi’an, China - [email protected] 3 Information Engineering University, Zhengzhou, China - [email protected] 4 Centre of TH-Satellite of China, Beijing, China - [email protected] Commission I, WG I/4 KEY WORDS: Star Sensor, Attitude Measurement, Error Analysis, On-Orbit Calibration, Angle between Cameras, On-orbit Monitoring Device ABSTRACT: On space remote sensing stereo mapping field, the angle variation between the star sensor’s optical axis and the earth observation camera’s optical axis on-orbit affects the positioning accuracy, when optical mapping is without ground control points (GCPs). This work analyses the formation factors and elimination methods for both the star sensor’s error and the angles error between the star sensor’s optical axis and the earth observation camera’s optical axis. Based on that, to improve the low attitude stability and long calibration time necessary of current satellite cameras, a method is then proposed for real-time on-orbit calibration of the angles between star sensor’s optical axis and the earth observation camera’s optical axis based on the principle of auto-collimation.
    [Show full text]
  • Space Policy Directive 1 New Shepard Flies Again 5
    BUSINESS | POLITICS | PERSPECTIVE DECEMBER 18, 2017 INSIDE ■ Space Policy Directive 1 ■ New Shepard fl ies again ■ 5 bold predictions for 2018 VISIT SPACENEWS.COM FOR THE LATEST IN SPACE NEWS INNOVATION THROUGH INSIGNT CONTENTS 12.18.17 DEPARTMENTS 3 QUICK TAKES 6 NEWS Blue Origin’s New Shepard flies again Trump establishes lunar landing goal 22 COMMENTARY John Casani An argument for space fission reactors 24 ON NATIONAL SECURITY Clouds of uncertainty over miltary space programs 26 COMMENTARY Rep. Brian Babin and Rep. Ami Ber We agree, Mr. President,. America should FEATURE return to the moon 27 COMMENTARY Rebecca Cowen- 9 Hirsch We honor the 10 Paving a clear “Path” to winners of the first interoperable SATCOM annual SpaceNews awards. 32 FOUST FORWARD Third time’s the charm? SpaceNews will not publish an issue Jan. 1. Our next issue will be Jan. 15. Visit SpaceNews.com, follow us on Twitter and sign up for our newsletters at SpaceNews.com/newsletters. ON THE COVER: SPACENEWS ILLUSTRATION THIS PAGE: SPACENEWS ILLUSTRATION FOLLOW US @SpaceNews_Inc Fb.com/SpaceNewslnc youtube.com/user/SpaceNewsInc linkedin.com/company/spacenews SPACENEWS.COM | 1 VOLUME 28 | ISSUE 25 | $4.95 $7.50 NONU.S. CHAIRMAN EDITORIAL CORRESPONDENTS ADVERTISING SUBSCRIBER SERVICES Felix H. Magowan EDITORINCHIEF SILICON VALLEY BUSINESS DEVELOPMENT DIRECTOR TOLL FREE IN U.S. [email protected] Brian Berger Debra Werner Paige McCullough Tel: +1-866-429-2199 Tel: +1-303-443-4360 [email protected] [email protected] [email protected] Fax: +1-845-267-3478 +1-571-356-9624 Tel: +1-571-278-4090 CEO LONDON OUTSIDE U.S.
    [Show full text]
  • Outstanding Expertise at the Service of Your Ambitions
    OUTSTANDING EXPERTISE AT THE SERVICE OF YOUR AMBITIONS #enablingyourambitions MILLION TURNOVER IN 2017 ambitions your EMPLOYEES INCLUDING ING 60% ENGINEERS OUR GOAL: L 70+ TO COMBINE‘‘ ENAB TECHNOLOGICAL EXCELLENCE AND 360 COMPETITIVENESS SODERN TO TRANSFORM OUR CUSTOMERS’ AMBITIONS 2 INTO REALITIES.‘‘ OUR DNA Franck Poirrier, CEO of Sodern We rely on more than 50 years of experience sharehoLDers: ArianeGroUP (90%) in optronics and neutron technology AND CEA (10%) 16600 to develop innovative and competitive solutions for our commercial and institutional customers. M2 OF FACILITIES 2 KEY AREAS As a subsidiary of the We preserve and enhance To meet the expectations of OF KNOW-HOW: European leader in access this exceptional technological changing markets, we set high OPTRONIC, to space, ArianeGroup, know-how by participating in competitive requirements for NEUtron we are operationally scientific programs that push ourselves: the implementation technoLOGY independent. the limits of the state of the of lean management, perfect art: the caesium atom clock understanding of our We are also a historical and Pharao, the seismometer of customers’ needs, agility and strategic defence supplier, a the Mars mission InSight, cells optimisation of production characteristic that guarantees of Pockels for the Megajoule costs are the commitments us a solid base of industrial laser, etc. that allow us to maintain a activities, thereby affirming competitive edge with a very durability and reliability. Sodern’s core business is the high level of customer Our institutional clients’ high series production of star satisfaction, and to consolidate level of requirements has led trackers that enable satellites our position as a world leader us to develop an extraordinary to orient themselves precisely in in several markets.
    [Show full text]
  • IASI: a Review of Instrument Performance and Characterizations
    IASI: a Review of Instrument Performance and Characterizations D. Siméonia, D. Blumsteinb, P. Astruca, C. Degrellea, B. Chetritea, B. Tournierd, G. Chalonb, T. Carlierb, G. Kayalc a ALCATEL SPACE -10 Bd du Midi BP99-06156 Cannes La Bocca Cedex - France, b CNES - 18 avenue Edouard Belin – 31401 Toulouse Cedex 9 – France c EUMETSAT – Am Kavalleriesant 31, D-64295 Darmstadt – Germany d NOVELTIS-Parc Tech du Canal – 2, av. de l’Europe – 31526 Ramonville St Agne Cedex-France Corporate Communications IASI Payload of the European Meteorological Polar-Orbit Satellites METOP Mains missions: weather predictions and climate studies. Program led by the French National Space Agency CNES in association with the European Meteorological Satellite Organization EUMETSAT. Prime Contractor: Thales Alenia Space Dimensions of sounder : 1.1x1.1x1.2 m3 Mass sounder < 200 Kg Stiffness > 55Hz during launch Power consumption < 200 Watt Reliability > 0.8 Availability > 97.5 % over 5 years 2 All rights reserved © 2007, Thales Alenia Space IASI Payload of the European Meteorological Polar-Orbit Satellites METOP Mains missions: weather predictions and climate studies. Program led by the French National Space Agency CNES in association with the European Meteorological Satellite Organization EUMETSAT. Prime Contractor: Thales Alenia Space Dimensions of sounder : 1.1x1.1x1.2 m3 Mass sounder < 200 Kg Stiffness > 55Hz during launch Power consumption < 200 Watt Reliability > 0.8 Availability > 97.5 % over 5 years Status : - EM delivered in Dec 2001 - PFM delivered in July
    [Show full text]
  • Esa Broch Envisat 2.Xpr Ir 36
    ENVISAT-1 Mission & System Summary ENVISAT-1 ENVISAT-1 Mission & System Summary Issue 2 Table of contents Table Table of contents 1 Introduction 3 Mission 4 System 8 Satellite 16 Payload Instruments 26 Products & Simulations 62 FOS 66 PDS 68 Overall Development and Verification Programme 74 Industrial Organization 78 Introduction Introduction 3 The impacts of mankind’s activities on the Earth’s environment is one of the major challenges facing the The -1 mission constists of three main elements: human race at the start of the third millennium. • the Polar Platform (); • the -1 Payload; The ecological consequences of human activities is of • the -1 Ground Segment. major concern, affecting all parts of the globe. Within less than a century, induced climate changes The development was initiated in 1989 as may be bigger than what those faced by humanity over a multimission platform; the -1 payload the last 10000 years. The ‘greenhouse effect’, acid rain, complement was approved in 1992 with the final the hole in the ozone layer, the systematic destruction decision concerning the industrial consortium being of forests are all triggering passionate debates. taken in March 1994. The -1 Ground Concept was approved in September 1994. This new awareness of the environmental and climatic changes that may be affecting our entire planet has These decisions resulted in three parallel industrial considerably increased scientific and political awareness developments, together producing the overall -1 of the need to analyse and understand the complex system. interactions between the Earth’s atmosphere, oceans, polar and land surfaces. The development, integration and test of the various elements are proceeding leading to a launch of the The perspective being able to make global observations -1 satellite planned for the end of this decade.
    [Show full text]
  • SPACE EXPLORATION SYMPOSIUM (A3) Mars Exploration – Part 2 (3B)
    64th International Astronautical Congress 2013 Paper ID: 18039 oral SPACE EXPLORATION SYMPOSIUM (A3) Mars Exploration { Part 2 (3B) Author: Mr. Gilles Lamour Sodern, France, [email protected] Mr. Jean-Baptiste Meurisse Sodern, France, [email protected] Mr. Christophe Stenvot Sodern, France, [email protected] Mr. Gilles Corlay Sodern, France, [email protected] Mr. S´ebastiende Raucourt Institut de Physique du Globe de Paris, France, [email protected] Mr. Philippe Laudet Centre National d'Etudes Spatiales (CNES), France, [email protected] Mr. Ren´ePerez Centre National d'Etudes Spatiales (CNES), France, [email protected] VBB SEISMOMETER FOR INSIGHT MISSION Abstract Sodern, as the industrial partner of IPGP (Institut de Physique du Globe de Paris) and CNES (French Space Agency), is developing the sensitive part of a new seismometer dedicated to Mars mission. This seismometer is a Very Broad Band seismometer to measure the Martian seismic activity. Sodern provides an inverted mechanical pendulum, called VBB pendulum, the movement of which being detected thanks to very accurate capacitive sensors. Three similar VBB axes are incorporated in the same package; the package is a sphere under vacuum to allow the best quality factor of the pendulum. Severe constraints of mass as far as hard environmental conditions have required a very thorough optimisation of the design. Breadboards have been manufactured and tested. They allow demonstrating the capability of the sphere to be embarked with the SEIS instrument onboard the NASA/JPL INSIGHT mission. This paper describes the architecture of the VBB and the Sphere and gives the performances as measured on ground and expected on Mars.
    [Show full text]
  • CLEO/P Assessment of a Jovian Moon Flyby Mission As Part of NASA Clipper Mission
    CDF STUDY REPORT CLEO/P Assessment of a Jovian Moon Flyby Mission as Part of NASA Clipper Mission CDF-154(D)Public April 2015 CLEO/P CDF Study Report: CDF-154(D) Public April 2015 page 1 of 198 CDF Study Report CLEO/P Assessment of a Jovian Moon Flyby Mission as Part of NASA Clipper Mission ESA UNCLASSIFIED – Releasable to the Public CLEO/P CDF Study Report: CDF-154(D) Public April 2015 page 2 of 198 FRONT COVER Study logo showing Orbiter and Jupiter with Moon ESA UNCLASSIFIED – Releasable to the Public CLEO/P CDF Study Report: CDF-154(D) Public April 2015 page 3 of 198 STUDY TEAM This study was performed in the ESTEC Concurrent Design Facility (CDF) by the following interdisciplinary team: TEAM LEADER R. Biesbroek, TEC-SYE AOGNC PAYLOAD COMMUNICATIONS POWER CONFIGURATION PROGRAMMATICS/ AIV COST PROPULSION RADIATION RISK DATA HANDLING SIMULATION GS&OPS STRUCTURES MISSION ANALYSIS SYSTEMS MECHANISMS THERMAL ESA UNCLASSIFIED – Releasable to the Public CLEO/P CDF Study Report: CDF-154(D) Public April 2015 page 4 of 198 This study is based on the ESA CDF Integrated Design Model (IDM), which is copyright 2004 – 2014 by ESA. All rights reserved. Further information and/or additional copies of the report can be requested from: T. Voirin ESA/ESTEC/SRE-FMP Postbus 299 2200 AG Noordwijk The Netherlands Tel: +31-(0)71-5653419 Fax: +31-(0)71-5654295 [email protected] For further information on the Concurrent Design Facility please contact: M. Bandecchi ESA/ESTEC/TEC-SYE Postbus 299 2200 AG Noordwijk The Netherlands Tel: +31-(0)71-5653701 Fax: +31-(0)71-5656024 [email protected] ESA UNCLASSIFIED – Releasable to the Public CLEO/P CDF Study Report: CDF-154(D) Public April 2015 page 5 of 198 TABLE OF CONTENTS 1 INTRODUCTION .................................................................................
    [Show full text]
  • → Paving the Way for Esa's Cosmic Vision Plan
    ESA’S CORE TECHNOLOGY PROGRAMME → PAVING THE WAY FOR ESA’S COSMIC VISION PLAN ESA/AOES Author: Georgia Bladon, EJR-Quartz ESA Designer: Sarah Poletti, ATG medialab Produced by: Communication, Outreach and Education Group Directorate of Science and Robotic Exploration European Space Agency Available online: sci.esa.int/core-technology-programme-brochure SRE-A-COEG-2015-001; September 2015 CCD 273 developed by e2v for Euclid. for e2v by 273developed CCD Cover image: Scientific themes for Cosmic Vision M4 candidate missions. ESA/ATG medialab ESA’S CORE TECHNOLOGY PROGRAMME → PAVING THE WAY FOR ESA’S COSMIC VISION PLAN → CONTENTS Cosmic Vision: The need for long-term planning 2 Building blocks of the Cosmic Vision Plan: Science missions 4 Core Technology Programme: Developing critical technology 6 L-Class missions 8 M-Class missions 10 Generic technology development 11 Programme benefits and participation 12 → INTRODUCTION This brochure acts as a guide to ESA’s Core Technology Programme and how it supports the Cosmic Vision Plan – ESA’s mechanism for the long-term planning of space science missions. The information featured here describes how the science directorate ensures that the technology needed to make these ground-breaking missions a reality is ready when needed. It also outlines the work the Core Technology Programme has already done toward some of the most ambitious missions in ESA’s history. 1 → COSMIC VISION: THE NEED FOR LONG-TERM PLANNING In order to achieve the goals of a broad scientific community, and ensure ESA is at the forefront of space exploration, long-term planning of space science missions is essential.
    [Show full text]
  • Facts & Figures
    OVERVIEW A specialised strategic sector _facts & figures 23rd edition, June 2019 Te European space industry in 2018 _f&f // 23rd edition, June 2019 // The European space industry in 2018 02 CONTENTS ABOUT EUROSPACE 01 OUTPUT OF THE EUROPEAN SPACE INDUSTRY IN 2018 35 FOREWORD 02 European spacecraft deliveries to launch 35 European spacecraft launched in 2018 35 OVERVIEW 03 Correlation between spacecraft mass A specialised strategic sector 03 at launch and industry revenues 37 Markets and customers 04 Ariane and VEGA launches 37 MAIN INDICATORS 06 METHODOLOGY 39 Long series indicators 07 Perimeter of the survey 39 Data Collection 39 SECTOR DEMOGRAPHICS 09 Consolidation Model 39 Industry employment - The need for consolidation 39 age and gender distribution 09 Methodological update in 2010 39 Industry employment - Qualification structure 09 Industry employment - distribution by country 10 DEFINITIONS 40 Industry employment - distribution by company 12 Space systems and related products Employment in large groups 12 considered in the survey 40 SMEs in the space sector 12 Launcher systems 40 Spacecraft/satellite systems 40 FINAL SALES BY MARKET SEGMENT 13 Ground Segment (and related services) 40 Overview: European sales vs. Export 13 Sector concentration: employment Overview - Public vs. Private customers 16 in space units, employment by unit and cumulated % 40 Customer details 17 Focus: SURVEY INFORMATION 41 European public/institutional customers 17 Eurospace economic model 41 Focus: The commercial market (private customers and exports)
    [Show full text]
  • EARTH OBSERVATION SYMPOSIUM (B1) Earth Observation Sensors and Technology (3) Author: Mr. Roland Le Goff Sodern, France, Roland
    67th International Astronautical Congress 2016 Paper ID: 34229 EARTH OBSERVATION SYMPOSIUM (B1) Earth Observation Sensors and Technology (3) Author: Mr. Roland Le Goff Sodern, France, roland.legoff@sodern.fr Mr. Guilhem Dubroca Sodern, France, [email protected] Mr. Didier Majcherczak Sodern, France, [email protected] Mr. Didier Loiseaux Sodern, France, [email protected] Mr. Martin Bauer Airbus DS GmbH, Germany, [email protected] Mr. Volker Kirschner European Space Agency (ESA), The Netherlands, [email protected] DESIGN OF SENTINEL-5 UV2VIS SPECTROMETER OPTIC Abstract The Sentinel-5 instrument, part of the joint ESA/European Union Earth observation programme COPERNICUS, is built by Airbus Defence Space GmbH. It is an assembly of Imaging spectrometers covering multiple spectral bands from 270nm to 2400nm. Sodern is developing the optics of the UV2VIS spectrometer (UV2VIS SO). It is part of the UV2VIS spectrometer, linking the slit - attached to the telescope - to the CCD array. It operates from 300nm to 500nm. This paper gives an overview of the design rules and few critical aspects of performances identified by Sodern during the phase B, thanks to the strong heritage in the design and manufacturing of state- of-the-art optical sub-assemblies of Imaging spectrometers, with programmes such as MERIS (on-board ESA ENVISAT satellite) and the Camera Optical Sub-Assembly (COSA) on-board Sentinel-3 Ocean and Land Colour Imager (OLCI). The following aspects have been investigated and will be discussed: implementation of a refractive optical prescription based on a grism (prism plus transmission grating) and use of iso-static mounts with epoxy bonding in order to overcome relatively large CTE mismatch between refractive lenses substrates, silica and CaF2, and titanium structure.
    [Show full text]
  • Using Infrared Based Relative Navigation for Active Debris Removal
    USING INFRARED BASED RELATIVE NAVIGATION FOR ACTIVE DEBRIS REMOVAL Ozg¨ un¨ Yılmaz(1), Nabil Aouf(1), Laurent Majewski(2), Manuel Sanchez-Gestido(3), Guillermo Ortega(3) (1) Cranfield University, Shrivenham United Kingdom, fo.yilmaz,n.aoufg@cranfield.ac.uk (2) SODERN, Limeil-Brevannes France, Email: [email protected] (3) European Space Agency, Noordwijk The Netherlands, Email: [email protected] ABSTRACT A debris-free space environment is becoming a necessity for current and future missions and ac- tivities planned in the coming years. The only means of sustaining the orbital environment at a safe level for strategic orbits (in particular Sun Synchronous Orbits, SSO) in the long term is by carrying out Active Debris Removal (ADR) at the rate of a few removals per year. Infrared (IR) technology has been used for a long time in Earth Observations but its use for navigation and guidance has not been subject of research and technology development so far in Europe. The ATV-5 LIRIS experiment in 2014 carrying a Commercial-of-The-Shelf (COTS) infrared sensor was a first step in de-risking the use of IR technology for objects detection in space. In this context, Cranfield University, SODERN and ESA are collaborating on a research to investigate the potential of IR-based relative navigation for debris removal systems. This paper reports the findings and developments in this field till date and the contributions from the three partners in this research. 1 INTRODUCTION The precise relative navigation of a chaser spacecraft towards a dead satellite is one of the most dif- ficult tasks to accomplish within an ADR mission, due to the fact that target is uncooperative and in general in an unknown state [1].
    [Show full text]