DOCSLIB.ORG

Space Debris Observations with the Slovak AGO70 Telescope: Astrometry and Light Curves

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Space Debris Observations with the Slovak AGO70 Telescope: Astrometry and Light Curves Available online at www.sciencedirect.com ScienceDirect Advances in Space Research 65 (2020) 2018–2035 www.elsevier.com/locate/asr Space debris observations with the Slovak AGO70 telescope: Astrometry and light curves Jirˇ´ı Sˇilha a,⇑, Stanislav Krajcˇovicˇ a, Matej Zigo a, Juraj To´th a, Danica Zˇ ilkova´ a, Pavel Zigo a, Leonard Kornosˇ a, Jaroslav Sˇimon a, Thomas Schildknecht b, Emiliano Cordelli b, Alessandro Vananti b, Harleen Kaur Mann b, Abdul Rachman b, Christophe Paccolat b, Tim Flohrer c a Comenius University, Faculty of Mathematics, Physics and Informatics, 84248 Bratislava, Slovakia b Astronomical Institute, University of Bern, CH-3012 Bern, Switzerland c ESA/ESOC, Space Debris Office, Robert-Bosch-Strasse 5, DE-64293 Darmstadt, Germany Received 5 July 2019; received in revised form 10 November 2019; accepted 25 January 2020 Available online 5 February 2020 Abstract The Faculty of Mathematics, Physics and Informatics of Comenius University in Bratislava, Slovakia (FMPI) operates its own 0.7-m Newtonian telescope (AGO70) dedicated to the space surveillance tracking and research, with an emphasis on space debris. The obser- vation planning focuses on objects on geosynchronous (GEO), eccentric (GTO and Molniya) and global navigation satellite system (GNSS) orbits. To verify the system’s capabilities, we conducted an observation campaign in 2017, 2018 and 2019 focused on astrometric and photometric measurements. In last two years we have built up a light curve catalogue of space debris which is now freely available for the scientific community. We report periodic signals extracted from more than 285 light curves of 226 individual objects. We con- structed phase diagrams for 153 light curves for which we obtained apparent amplitudes. Ó 2020 COSPAR. Published by Elsevier Ltd. All rights reserved. Keywords: Space debris; Optical measurements; Space surveillance; Light curve; Catalogue; GEO; GTO; HEO 2010 MSC: 00-01; 99-00 1. Introduction The demand for Space Situational Awareness (SSA) is constantly growing due to the increase of the space traffic ⇑ Corresponding author. which is now largely joined by private sector which oper- E-mail addresses: [email protected] (J. Sˇilha), stanislav.krajcovic ates its own launchers and satellites (del Portillo et al., @fmph.uniba.sk (S. Krajcˇovicˇ), [email protected] (M. Zigo), 2019; May et al., 2018). In order to have the usage of space [email protected] (J. To´th), [email protected] (P. Zigo), sustainable understand how debris is created, active debris [email protected] (L. Kornosˇ), [email protected]. removal, and the real time and high quality data acquisi- sk (J. Sˇimon), [email protected] (T. Schildknecht), [email protected] (E. Cordelli), alessandro.vananti@aiub. tion is a necessity. Space debris is situated on various types unibe.ch (A. Vananti), [email protected] (H.K. Mann), of geocentric orbits, from low Earth orbits (LEO) of sev- [email protected] (A. Rachman), christophe.paccolat@aiub. eral hundreds kilometres above the Earth’s surface to unibe.ch (C. Paccolat), tim.fl[email protected] (T. Flohrer). https://doi.org/10.1016/j.asr.2020.01.038 0273-1177/Ó 2020 COSPAR. Published by Elsevier Ltd. All rights reserved. J. Sˇ ilha et al. / Advances in Space Research 65 (2020) 2018–2035 2019 geosynchronous Earth orbits (GEO) at the heights of SST is responsible for regular tracking by using optical about 35,800 km above the surface. The regular monitoring (passive and active) and radar systems. This service and cataloguing of debris through the Space Surveillance requires orbit determination function and maintenance of and Tracking (SST) systems helps to identify and prevent a catalogue. SST requires access to a network of sensors possible collisions with operational infrastructure. The implying real-time data acquisition and processing (Silha majority of observation data comes from radar and optical et al., 2019). passive sensors but inclusion of the Satellite Laser Ranging (SLR) systems to the observations of non-active satellites 1.2. Optical networks and single systems and upper stages is also being considered (Shappirio et al., 2016; Konacki et al., 2016). The primary source of orbital elements data for cata- The research of space debris investigates the popula- logued space debris is the Space Surveillance Network tion’s dynamical (e.g. orbital elements) and physical prop- (SSN). The SSN consists of dozens ground-based radar erties (e.g. surface material). It covers wide range of topics and optical sensors and one space-based optical sensor including the survey and cataloguing (Schildknecht et al., (Raley et al., 2016; Abbasi et al., 2019). It covers all orbital 2004; Molotov et al., 2008; Fiedler et al., 2019), attitude regions, from LEO up to High Earth Orbits (HEO), and its determination (e.g. through light curves) (Williams, 1979; catalogue contains the mean osculating elements in a form Santoni et al., 2013) to support the debris mitigation efforts of TLE (Two-Line Elements) publicly available at (Liou et al., 2010; Forshaw et al., 2017; Wang et al., 2018) (Network, 2019). and anomalous behaviour of the object (Slatton and The largest civilian network performing the SST func- Mckissock, 2017), deals with the models of the spatial dis- tion is the International Scientific Optical Network (ISON) tribution for small populations (from lm to cm) (Krisko operated by the Keldych Institute of Applied Mathematics, et al., 2015) and analyzes the surface properties of the Russian Academy of Sciences, Russia. There are more than object (Vananti et al., 2017; Cardona et al., 2016; Lu three dozen of observation facilities worldwide contribut- et al., 2017). ing to the ISON network (Molotov et al., 2008, 2017). Sev- In recent years several European countries increased eral other networks perform the SST functionality their efforts toward partial independence of SST capabili- including: Russian network of Automated Warning System ties (e.g. observations of GEO population) from the inter- on Hazardous Situations in Outer Space (ASPOS OKP) national partners, e.g. USA and Russian Federation. These center (Agapov et al., 2018), SMARTNET (Fiedler et al., efforts can be demonstrated through the establishment of 2019) and OWL (Park et al., 2018). European Space Agency’s (ESA’s) SSA programme with A single sensor is not able to cover any of the popula- a SST segment addressing technology developments for tions from LEO up to HEO completely and is usually used monitoring space debris. A part of the ESA SST is the to acquire statistical information about a specific orbital Coordination Expert Center which will be responsible for region by using sky surveys, or to acquire scientific data the interfaces between heterogeneous sensors and the cata- for a specific object. Well established sensors are, for exam- loguing function of the SST segment (Jilete et al., 2019; ple, ESA OGS (Spain) (Schildknecht et al., 2004) and Silha et al., 2017). Additionally, in 2015, the European NASA MODEST (Chile) (Seitzer et al., 2004) which both Commission established its own EU SST Support Frame- dedicate their observation program to the continuous sur- work governed through the EU SST consortium which veys of the GEO ring, or ZIMLAT (Switzerland) system of now consists of eight EU countries (Morand et al., 2018). the Astronomical Institute of the University of Bern Any effort to perform SST functions require a sufficient (AIUB) used for optical observations of debris and Near network of sensors, both radar and optical, in order to get Earth Asteroids (NEA) (Silha et al., 2018). This system also a wide coverage, suitable frequency of observations per cooperates with the aforementioned networks such as object and continuous data flow into the system. Slovak ISON and SMARTNET to which ZIMLAT has estab- Republic, as a member of EU and prospectively future lished interfaces. member of ESA, expressed its interest to participate in the European SST programs, as well in space debris 1.3. Data products research, by focusing on astrometric and photometric data acquisition with optical passive sensors (Silha et al., 2019). As for the SST applications, the optical measurements provide several different products. The most important 1.1. Optical measurements for the maintenance of a catalogue and monitoring of the system’s performance are the astrometric measurements There are two major observations strategies recognized which contain the relative position of the object compared for optical passive observations of space debris. Optical to the star background. The astrometric measurements are surveys aim to discover new objects for cataloguing or to usually provided in spherical equatorial coordinates with get statistical information like the object’s brightness distri- reference epoch in J2000. The data format is usually Con- bution or orbital plane. Tracking (follow-up) observations sultative Committee for Space Data Systems (CCSDS) are carried out for orbit determination and debris research. Tracking Data Message (TDM) format (The Consultative 2020 J. Sˇ ilha et al. / Advances in Space Research 65 (2020) 2018–2035 Committee for Space Data Systems, 2017) or Minor Planet (Schildknecht et al., 2004). The presented system is a New- Center (MPC) format (MPC, 2019a,b). tonian design telescope with a very thin parabolic mirror Photometry is performed in order to acquire informa- with diameter of 700 mm from Alluna optics with sup- tion about physical characteristics of an object. One can ported by gravity actuator. The focal length of the system study the rotation properties of an object through the light is 2962.0 mm. The CCD sensor is the FLI Proline PL1001 curves, method often used in minor planet domain (Pravec Grade 1 CCD camera with 1024 Â 1024 pixels and 24 lm et al., 2005; MMT, 2019; Pontieu, 1997; Silha et al., 2018). pixel size which results in an effective field-of-view (FoV) Light curve is a consecutive series of brightness measure- of 28:50 Â 28:50 and effective iFoV of 1:6700=pixel.
Load more

Recommended publications
  • OUFTI-1 Environmental Impact Assessment
    Date: 11/02/2016 Issue: 1 Rev: 1 Page: 1 of 11 OUFTI-1 Environmental Impact Assessment Reference 3_OUF_ENV_IMPACT_1.0 Issue/Rev Issue 1 Rev 0 Date 11/02/2016 Distribution OUFTI-1 team OUFTI-1 Environmental Impact Assessment Date: 11/02/2016 Issue: 1 Rev: 1 Page: 2 of 11 AUTHORS Name Email Telephone X. Werner [email protected] +32 4 366 37 38 S. De Dijcker [email protected] +32 4 366 37 38 RECORD OF REVISIONS Iss/Rev Date Author Section/page Change description 1/0 11/02/2016 X.Werner, All Initial issue S. De Dijcker Copyright University of Liège [2016]. OUFTI-1 Environmental Impact Assessment Date: 11/02/2016 Issue: 1 Rev: 1 Page: 3 of 11 TABLE OF CONTENTS Authors ....................................................................................................................................... 2 Record of revisions ..................................................................................................................... 2 1. Activities and Objectives ................................................................................................... 4 1.1. Project description ....................................................................................................... 4 1.2. Soyuz launch vehicle ................................................................................................... 5 1.3. Arianespace ................................................................................................................. 7 1.4. Conclusion ..................................................................................................................
    [Show full text]
  • Design for Demise Analysis for Launch Vehicles
    A first design for demise analysis for launch vehicles Henrik Simon, Stijn Lemmens Space debris: Inactive, manmade objects in space Source: ESA Overview Introduction Fundamentals Modelling approach Results and discussion Summary and outlook What is the motivation and task? INTRODUCTION Motivation . Mitigation: Prevention of creation and limitation of long-term presence . Guidelines: LEO removal within 25 years . LEO removal within 25 years after mission end . Casualty risk limit for re-entry: 1 in 10,000 Rising altitude Decay & re-entry above 2000 km Source: NASA Source: NASA Solution: Design for demise Source: ESA Scope of the thesis . Typical design of upper stages . General Risk assessment . Design for demise solutions to reduce the risk ? ? ? Risk A Risk B Risk C Source: CNES How do we assess the risk and simulate the re-entry? FUNDAMENTALS Fundamentals: Ground risk assessment Ah = + 2 Ai � ℎ = =1 � Source: NASA Source: NASA 3.5 m 5.0 m 2 2 ≈ ≈ Fundamentals: Re-entry simulation tools SCARAB: Spacecraft-oriented approach . CAD-like modelling . 6 DoF flight dynamics . Break-up / fragmentation computed How does a rocket upper stage look like? MODELLING Modelling approach . Research on typical design: . Elongated . Platform . Solid Rocket Motor . Lack of information: . Create common intersection . Deliberately stay top-level and only compare effects Modelling approach Modelling approach 12 Length [m] 9 7 5 3 2 150 300 500 700 800 1500 2200 Mass [kg] How much is the risk and how can we reduce it? SIMULATIONS Example of SCARAB re-entry simulation 6x Casualty risk of all reference cases Typical survivors Smaller Smaller fragments fragments Pressure tanks Pressure tanks Main tank Engine Main structure + tanks Design for Demise .
    [Show full text]
  • Enabling Interstellar Probe
    This article appeared in a journal published by Elsevier. The attached copy is furnished to the author for internal non-commercial research and education use, including for instruction at the authors institution and sharing with colleagues. Other uses, including reproduction and distribution, or selling or licensing copies, or posting to personal, institutional or third party websites are prohibited. In most cases authors are permitted to post their version of the article (e.g. in Word or Tex form) to their personal website or institutional repository. Authors requiring further information regarding Elsevier’s archiving and manuscript policies are encouraged to visit: http://www.elsevier.com/copyright Author's personal copy Acta Astronautica 68 (2011) 790–801 Contents lists available at ScienceDirect Acta Astronautica journal homepage: www.elsevier.com/locate/actaastro Enabling interstellar probe Ralph L. McNutt Jr.a,n, Robert F. Wimmer-Schweingruber b,1, the International Interstellar Probe Team a The Johns Hopkins University Applied Physics Laboratory, 11100 Johns Hopkins Road, M/S MP3-E128, Laurel, MD 20723, USA b Institut fuer Experimentelle und Angewandte Physik, University of Kiel, Leibnizstrasse 11, D-24118 Kiel, Germany article info abstract Article history: The scientific community has advocated a scientific probe to the interstellar medium for Received 15 February 2010 over 30 years. While the Voyager spacecraft have passed through the termination shock Received in revised form of the solar wind, they have limited lifetimes as their radioisotope power supplies 16 June 2010 decay. It remains unclear whether they can reach the heliopause, the boundary between Accepted 2 July 2010 shocked solar wind and interstellar plasmas, and, in any case, they will not reach the Available online 17 August 2010 undisturbed interstellar medium.
    [Show full text]
  • Download Paper
    GIOVE-A’S FREGAT DISPOSAL ASSESSMENT D. Navarro-Reyes(1), R. Zandbergen(2), D. Escobar(3) (1)ESA/ESTEC, Keplerlaan 1, 2200 AG Noordwijk, The Netherlands, Email: [email protected] (2) ESA/ESOC, Robert-Bosch-Str. 5, D-64293 Darmstadt, Germany, Email: [email protected] (3)GMV at ESOC, ESA/ESOC Robert-Bosch-Str. 5, D-64293 Darmstadt, Germany, Email: [email protected] ABSTRACT dedicated stations deployed around the world. The Galileo constellation is defined as a Walker 27/3/1 and is composed of 3 equally-spaced orbital planes with a Galileo will be Europe’s own global navigation satellite nominal inclination of 56 degrees and a semi-major axis system, providing a highly accurate, guaranteed global of 29,600 km. Each plane will contain nine equally- positioning service under civilian control. Following the spaced satellites plus a spare satellite. The first launches approval of Galileo in 1999, a demonstration element are foreseen in 2010, with the full constellation was added – the Galileo System Test Bed (GSTB) with deployed by end 2013. the GIOVE-A and GIOVE-B satellites – to allow early experimentation with the navigation signals and services Following the approval of Galileo in 1999, a before committing to the final constellation design. demonstration element was added – the Galileo System Test Bed (GSTB) with the GIOVE-A and GIOVE-B GIOVE-A (launched on 28 Dec 2005) and GIOVE-B satellites, whose mission was: (launched on 26 April 2008) were injected in the Galileo operational orbit (semi-major axis 29600 km, x To secure use of the frequencies allocated by the circular orbit, inclination 56 degrees) by direct injection International Telecommunications Union (ITU) for with Soyuz/FREGAT launch vehicle.
    [Show full text]
  • Please Type Your Paper Title Here In
    Estimating the Reliability of a Soyuz Spacecraft Mission Michael G. Lutomskia*, Steven J. Farnham IIb, and Warren C. Grantb aNASA-JSC, Houston, TX – [email protected] bARES Corporation, Houston, TX Abstract: Once the US Space Shuttle retires in 2010, the Russian Soyuz Launcher and Soyuz Spacecraft will comprise the only means for crew transportation to and from the International Space Station (ISS). The U.S. Government and NASA have contracted for crew transportation services to the ISS with Russia. The resulting implications for the US space program including issues such as astronaut safety must be carefully considered. Are the astronauts and cosmonauts safer on the Soyuz than the Space Shuttle system? Is the Soyuz launch system more robust than the Space Shuttle? Is it safer to continue to fly the 30 year old Shuttle fleet for crew transportation and cargo resupply than the Soyuz? Should we extend the life of the Shuttle Program? How does the development of the Orion/Ares crew transportation system affect these decisions? The Soyuz launcher has been in operation for over 40 years. There have been only two loss of life incidents and two loss of mission incidents. Given that the most recent incident took place in 1983, how do we determine current reliability of the system? Do failures of unmanned Soyuz rockets impact the reliability of the currently operational man-rated launcher? Does the Soyuz exhibit characteristics that demonstrate reliability growth and how would that be reflected in future estimates of success? NASA’s next manned rocket and spacecraft development project is currently underway.
    [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]
  • 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]
  • Here the Italian Space Agency ASI Holds 30% of the Shares and the Rest Is the Property of Avio Spa
    Goliat the first Romanian satellite is approaching the launch date- less than 6 months since Romania will have its first space mission At a recent press conference, Jean-Yves Le Gall the director of ArianeSpace, shared with the public the plans of the company for 2011. Like for the last year we will have a busy schedule with not less than 12 launches (double than for 2010). As before the central point will be the veteran Ariane 5 rocket, but part of the new managerial strategy, ArianeSpace will look also for the segment of medium and small launchers meeting the demands of the worldwide customers. It is hoped that some part of the operations will be transferred gradually to these niches and thus to be over passed the record set last year when approximately 60% of the world GEO telecom satellites have been launched by ArianeSpace. The perspectives are very good with another 12 additional GEO transfer contracts being signed in 2010 (about 63% from the international commercial market). The technical procedures which make sure these flights are accomplished are also at the highest standards (proved by the last 3 launches of 2010 separated by one month each i.e. October, November and December) and the Ariane 5 rocket, because of the proven reliability has became today the preferred of the commercial launches (since December 2002 when the version ECA has been put into operation and when the inaugural flight ended by loosing the 2 satellite transported onboard-Stentor and Hot Bird 7- the rocket has an impressive record of 36 successful flights).
    [Show full text]
  • Failures in Spacecraft Systems: an Analysis from The
    FAILURES IN SPACECRAFT SYSTEMS: AN ANALYSIS FROM THE PERSPECTIVE OF DECISION MAKING A Thesis Submitted to the Faculty of Purdue University by Vikranth R. Kattakuri In Partial Fulfillment of the Requirements for the Degree of Master of Science in Mechanical Engineering August 2019 Purdue University West Lafayette, Indiana ii THE PURDUE UNIVERSITY GRADUATE SCHOOL STATEMENT OF THESIS APPROVAL Dr. Jitesh H. Panchal, Chair School of Mechanical Engineering Dr. Ilias Bilionis School of Mechanical Engineering Dr. William Crossley School of Aeronautics and Astronautics Approved by: Dr. Jay P. Gore Associate Head of Graduate Studies iii ACKNOWLEDGMENTS I am extremely grateful to my advisor Prof. Jitesh Panchal for his patient guidance throughout the two years of my studies. I am indebted to him for considering me to be a part of his research group and for providing this opportunity to work in the fields of systems engineering and mechanical design for a period of 2 years. Being a research and teaching assistant under him had been a rewarding experience. Without his valuable insights, this work would not only have been possible, but also inconceivable. I would like to thank my co-advisor Prof. Ilias Bilionis for his valuable inputs, timely guidance and extremely engaging research meetings. I thank my committee member, Prof. William Crossley for his interest in my work. I had a great opportunity to attend all three courses taught by my committee members and they are the best among all the courses I had at Purdue. I would like to thank my mentors Dr. Jagannath Raju of Systemantics India Pri- vate Limited and Prof.
    [Show full text]
  • U S E R M a N U
    •Introduction 6/04/01 11:09 Page 1 SOYUZ USER’ S MANUAL ST-GTD-SUM-01 - ISSUE 3 - REVISION 0 - APRIL 2001 © Starsem 2001. All rights reserved. •Introduction 6/04/01 11:09 Page 2 •Introduction 6/04/01 11:09 Page 3 SOYUZ USER’S MANUAL ST-GTD-SUM-01 ISSUE 3, REVISION 0 APRIL 2001 FOREWORD Starsem is a Russian-European joint venture founded in 1996 that is charged with the commercialization of launch services using the Soyuz launch vehicle, the most frequently launched rocket in the world and the only manned vehicle offered for commercial space launches. Starsem headquarters are located in Paris, France and the Soyuz is launched from the Baikonour Cosmodrome in the Republic of Kazakhstan. Starsem is a partnership with 50% European and 50% Russian ownership. Its shareholders are the European Aeronautic, Defence, and Space Company, EADS (35%), Arianespace (15%), the Russian Aeronautics and Space Agency, Rosaviacosmos (25%), and the Samara Space Center, TsSKB-Progress (25%). Starsem is the sole organization entrusted to finance, market, and conduct the commercial sale of the Soyuz launch vehicle family, including future upgrades such as the Soyuz/ST. Page3 •Introduction 6/04/01 11:09 Page 4 SOYUZ USER’S MANUAL ST-GTD-SUM-01 ISSUE 3, REVISION 0 APRIL 2001 REVISION CONTROL SHEET Revision Date Revision No. Change Description 1996 Issue 1, Revision 0 New issue June 1997 Issue 2, Revision 0 Complete update April 2001 Issue 3, Revision 0 Complete update ST-GTD-SUM-01 General modifications that reflect successful flights in 1999-2000 and Starsem’s future development plans.
    [Show full text]
  • Space Activities 2018
    Space Activities in 2018 Jonathan McDowell [email protected] 2019 Feb 20 Rev 1.4 Preface In this paper I present some statistics characterizing astronautical activity in calendar year 2018. In the 2014 edition of this review, I described my methodological approach and some issues of definitional ambguity; that discussion is not repeated here, and it is assumed that the reader has consulted the earlier document, available at http://planet4589.org/space/papers/space14.pdf (This paper may be found as space18.pdf at the same location). Orbital Launch Attempts During 2018 there were 114 orbital launch attempts, with 112 reaching orbit. Table 1: Orbital Launch Attempts 2009-2013 2014 2015 2016 2017 2018 Average USA 19.0 24 20 22 30 31 Russia 30.2 32 26 17 19 17 China 14.8 16 19 22 18 39 Europe 11 12 11 11 11 Japan 4 4 4 7 6 India 4 5 7 5 7 Israel 1 0 1 0 0 N Korea 0 0 1 0 0 S Korea 0 0 0 0 0 Iran 0 1 0 1 0 New Zealand 0 0 0 0 3 Other 9 10 13 13 16 Total 79.0 92 87 85 91 114 The Arianespace-managed Soyuz launches from French Guiana are counted as European. Electron is licensed in the USA but launched from New Zealand territory. However, in late 2018 New Zealand registered the upper stages from the Jan 2018 Electron launch with the UN. Based on this, in rev 1.4 of this document I am changing Electron to count as a New Zealand launch vehicle.
    [Show full text]
  • The Physics of Space Security a Reference Manual
    THE PHYSICS The Physics of OF S P Space Security ACE SECURITY A Reference Manual David Wright, Laura Grego, and Lisbeth Gronlund WRIGHT , GREGO , AND GRONLUND RECONSIDERING THE RULES OF SPACE PROJECT RECONSIDERING THE RULES OF SPACE PROJECT 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page ii 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page iii The Physics of Space Security a reference manual David Wright, Laura Grego, and Lisbeth Gronlund 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page iv © 2005 by David Wright, Laura Grego, and Lisbeth Gronlund All rights reserved. ISBN#: 0-87724-047-7 The views expressed in this volume are those held by each contributor and are not necessarily those of the Officers and Fellows of the American Academy of Arts and Sciences. Please direct inquiries to: American Academy of Arts and Sciences 136 Irving Street Cambridge, MA 02138-1996 Telephone: (617) 576-5000 Fax: (617) 576-5050 Email: [email protected] Visit our website at www.amacad.org or Union of Concerned Scientists Two Brattle Square Cambridge, MA 02138-3780 Telephone: (617) 547-5552 Fax: (617) 864-9405 www.ucsusa.org Cover photo: Space Station over the Ionian Sea © NASA 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page v Contents xi PREFACE 1 SECTION 1 Introduction 5 SECTION 2 Policy-Relevant Implications 13 SECTION 3 Technical Implications and General Conclusions 19 SECTION 4 The Basics of Satellite Orbits 29 SECTION 5 Types of Orbits, or Why Satellites Are Where They Are 49 SECTION 6 Maneuvering in Space 69 SECTION 7 Implications of
    [Show full text]