DOCSLIB.ORG

Technical and Economic Feasibility of Telerobotic On-Orbit Satellite Servicing

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Technical and Economic Feasibility of Telerobotic On-Orbit Satellite Servicing ABSTRACT Title of Dissertation: TECHNICAL AND ECONOMIC FEASIBILITY OF TELEROBOTIC ON-ORBIT SATELLITE SERVICING Brook Rowland Sullivan, Doctor of Philosophy, 2005 Dissertation directed by: Professor David L. Akin Department of Aerospace Engineering Space Systems Laboratory University of Maryland The aim of this research is to devise an improved method for evaluating the techni- cal and economic feasibility of telerobotic on-orbit satellite servicing scenarios. Past, present, and future telerobotic on-orbit servicing systems and their key capabilities are examined. Previous technical and economic analyses of satellite servicing are re- viewed and evaluated. The standard method employed by previous feasibility studies is extended, developing a new servicing decision approach incorporating operational uncertainties (launch, docking, et cetera). Comprehensive databases of satellite char- acteristics and on-orbit failures are developed to provide input to the expected value evaluation of the servicing versus no-servicing decision. Past satellite failures are re- viewed and analyzed, including the economic impact of those satellite failures. Oppor- tunities for spacecraft life extension are also determined. Servicing markets of various types are identified and detailed using the results of the database analysis and the new, expected-value-based servicing feasibility method. This expected value market assessment provides a standard basis for satellite servicing decision-making for any proposed servicing architecture. Finally, the method is demonstrated by evaluating a proposed small, lightweight servicer providing retirement services for geosynchronous spacecraft. An additional benefit of the method is that it enables parametric analysis of the sensitivity of economic viability to the probability of docking success, thus establishing a threshold for that critical value. While based on a more economically conservative approach, the new method demonstrates the feasibility of the proposed server in the face of operational uncertainties. TECHNICAL AND ECONOMIC FEASIBILITY OF TELEROBOTIC ON-ORBIT SATELLITE SERVICING by Brook Rowland Sullivan Dissertation submitted to the Faculty of the Graduate School of the University of Maryland, College Park in partial fulfillment of the requirements for the degree of Doctor of Philosophy 2005 Advisory Committee: Professor David L. Akin, Chairman/Advisor Professor Mark Austin Dr. Craig R. Carignan Professor Roberto Celi Professor M. Robert Sanner Copyright by University of Maryland Space Systems Laboratory Brook Rowland Sullivan 2005 PREFACE “Looks like your vehicle is out of gas. Would you like to buy a new one?” There has got to be a better way. ii DEDICATION To Mom & Dad and Eve, This dissertation is built upon your unwavering support, unflagging encouragement, and sustaining love. And to Debbie, Sissy, and David, Gone too soon. Dearly missed. iii ACKNOWLEDGEMENTS Many people contributed to the existence of this dissertation. Firstly, I owe thanks to Dr. Dave Akin and to David Lavery for the opportunity to work at one of the most interesting places on the planet. Thanks as well to my very patient committee members. My time at the lab started with a suggestion from Joe Parrish - thanks, I think. I also received all manner of assistance and encouragement from my lab-mates (Craig, Russ, Maki, JM, Lisa, Robs, Steves, Corde, Debbie, Mikes, and Adam) and office- mates (Evie, Sarah, and Joe). Thanks also to Kiwi, Glen, Claudia, Julianne, Brian, Phil, and Gardell for inspiration along the way. Particular thanks to Jeff Smithanik and Jeff Braden for spending a few weeks asking, “What if?” Late in the research process, Dr. Owen Brown, Dr. Albert Bosse, and Dr. Gordon Roesler asked some very good questions that led in useful directions. Thanks. And a special thanks to Dr. Mary Bowden for keeping this on the administrative rails right up to the very end. The final production of this document was ably abetted by Sarah Hall, Suneel Sheikh, Stephen Roderick, and my excellent wife, Eve. iv TABLE OF CONTENTS List of Tables xii List of Figures xvii List of Abbreviations xxiii 1 Introduction 1 1.1 Motivations . 1 1.1.1 On-Orbit Failures . 2 1.1.2 Spacecraft Life Extension . 3 1.1.3 Other Servicing Opportunities . 4 1.1.4 Advancing Robotic Capabilities . 4 1.1.5 New Launch Alternatives . 6 1.2 Dissertation Overview . 7 1.3 Contributions . 8 2 Background 10 2.1 The Satellite Servicing Problem . 10 2.1.1 Servicing Failures . 13 2.1.2 Spacecraft Lifetime Extension . 15 2.1.3 Other Services . 16 2.2 A Brief History Of On-Orbit Servicing . 17 v 2.2.1 Space Shuttle Based Satellite Servicing Missions . 17 2.2.2 Satellite Self Rescues . 20 2.2.3 Space Shuttle Based Servicing Technology Demonstrations . 20 2.2.4 Other On-Orbit Servicing Technology Demonstrations . 22 2.3 Future Servicing Technology Demonstrations . 23 2.3.1 Future Servicing Technology Flight Missions . 23 2.3.2 Dexterous Robotic Servicing Research Programs . 27 2.4 Robotic Serviceability Of Satellites . 28 2.4.1 Target Satellites . 28 2.4.2 Servicers . 29 3 Previous Satellite Servicing Economic Models 35 3.1 1981 - Manger . 35 3.2 1981 - Vandenkerckhove . 41 3.3 1985 - Vandenkerckhove . 43 3.4 1989 - Yasaka . 46 3.5 1992 - The INTEC Study . 48 3.6 1994 - Newman . 50 3.7 1996 - Hibbard . 54 3.8 1998 - Davinic . 56 3.9 1999 - Leisman . 57 3.10 2001 - Lamassoure . 59 3.11 2002 - McVey . 59 3.12 2004 - Walton . 60 3.13 Other Economic Studies . 61 3.14 Cost Estimation Methods . 62 3.15 Evaluation Of Previous Studies . 64 vi 3.15.1 Operational Uncertainty . 64 3.15.2 Comprehensive Market Assessment . 65 3.15.3 Decoupling Market Assessment From Servicer Design . 65 4 A New Method To Evaluate Servicing Feasibility 66 4.1 Previous Servicing Decision Method . 66 4.2 Expected Value Method . 67 4.3 New Servicing Decision Method . 69 4.4 Satellite Information Required For New Method . 70 5 Database Development 71 5.1 Spacecraft Information Database . 72 5.1.1 Spacecraft Identification Scheme . 72 5.1.2 Sources . 73 5.1.3 Fields . 74 5.2 Database of On-Orbit Spacecraft Failures . 79 5.2.1 Failures Identification Scheme . 79 5.2.2 Sources . 80 5.2.3 Fields . 80 6 Satellite Trends 82 6.1 Commercial Geosynchronous Communications Satellites . 82 6.2 Transponders Per Commercial Geosynchronous Communications Satel- lite..................................... 84 6.3 Total Commercial Geosynchronous Communications Satellite Transpon- ders .................................... 85 6.4 Bandwidth Per Transponder . 86 6.5 Stabilization Of Commercial Geosynchronous Communication Satellites 88 vii 6.6 Geosynchronous Communication Satellite Buses . 90 6.7 Commercial Geosynchronous Communications Satellite Design Life . 92 6.8 Bandwidth-Design Life Trends . 93 6.9 Failure Rate . 96 7 On-Orbit Servicing Opportunities 99 7.1 Launches And Payloads . 99 7.2 Economic Impact Of On-Orbit Satellite Failures . 102 7.3 Spacecraft Failure Servicing Opportunities . 105 7.3.1 Wrong Orbit . 105 7.3.2 Deployment Problems . 112 7.3.3 Component Failures . 112 7.3.4 Fuel Depletion . 116 7.3.5 Other Failures . 116 7.3.6 Spacecraft Family Anomalies . 119 7.3.7 Failed Spacecraft Relocation . 122 7.3.8 Observations Concerning Serviceable Failures . 126 7.4 Spacecraft Lifetime Extension . 129 7.4.1 Relocation . 129 7.4.2 Refueling . 137 7.4.3 Consumables Replenishment . 140 7.4.4 Preventative Maintenance . 141 7.4.5 Spacecraft Upgrade . 142 7.4.6 Optical Surface Maintenance . 142 7.5 Other Services . 144 7.5.1 Inspection . 144 7.5.2 Debris And Failed Spacecraft Relocation . 145 viii 7.6 Summary Of Opportunities . 149 8 Expected Value Of Servicing Market Segments 150 8.1 Chance Node Probabilities . 152 8.1.1 Launch Outcomes . 152 8.1.2 Orbital Transfer Outcomes . 154 8.1.3 Graveyard Transfer Outcomes . 154 8.1.4 Deployment Outcomes . 155 8.1.5 Docking Outcomes . 156 8.1.6 Undocking Outcomes . 156 8.1.7 Refueling Outcomes . 157 8.1.8 Dexterous Repair Outcomes . 158 8.2 Servicing Mission Expected Values . 159 8.2.1 Retirement Maneuver . 159 8.2.2 LEO to GEO Transfer . 167 8.2.3 Relocate In GEO . 171 8.2.4 Refuel . 174 8.2.5 ORU-Like Replacement . 177 8.2.6 General Repair . 180 8.2.7 Deployment Assistance . 181 8.2.8 Deployment Monitoring . 184 8.2.9 Remove Inactive . 187 8.2.10 Health Monitoring . 190 8.3 Summary Of Servicing Mission Expected Values . 190 8.4 Robotic Complexity . 192 9 Demonstration Of The New Method 196 9.1 Servicer Description . 196 ix 9.2 Servicer Operations Concept . 199 9.3 Application Of The New Feasibility Methodology . 204 10 Conclusion 215 10.1 Results . 215 10.1.1 Assessment Of Previous Studies . ..
Load more

Recommended publications
  • Astrodynamics
    Politecnico di Torino SEEDS SpacE Exploration and Development Systems Astrodynamics II Edition 2006 - 07 - Ver. 2.0.1 Author: Guido Colasurdo Dipartimento di Energetica Teacher: Giulio Avanzini Dipartimento di Ingegneria Aeronautica e Spaziale e-mail: [email protected] Contents 1 Two–Body Orbital Mechanics 1 1.1 BirthofAstrodynamics: Kepler’sLaws. ......... 1 1.2 Newton’sLawsofMotion ............................ ... 2 1.3 Newton’s Law of Universal Gravitation . ......... 3 1.4 The n–BodyProblem ................................. 4 1.5 Equation of Motion in the Two-Body Problem . ....... 5 1.6 PotentialEnergy ................................. ... 6 1.7 ConstantsoftheMotion . .. .. .. .. .. .. .. .. .... 7 1.8 TrajectoryEquation .............................. .... 8 1.9 ConicSections ................................... 8 1.10 Relating Energy and Semi-major Axis . ........ 9 2 Two-Dimensional Analysis of Motion 11 2.1 ReferenceFrames................................. 11 2.2 Velocity and acceleration components . ......... 12 2.3 First-Order Scalar Equations of Motion . ......... 12 2.4 PerifocalReferenceFrame . ...... 13 2.5 FlightPathAngle ................................. 14 2.6 EllipticalOrbits................................ ..... 15 2.6.1 Geometry of an Elliptical Orbit . ..... 15 2.6.2 Period of an Elliptical Orbit . ..... 16 2.7 Time–of–Flight on the Elliptical Orbit . .......... 16 2.8 Extensiontohyperbolaandparabola. ........ 18 2.9 Circular and Escape Velocity, Hyperbolic Excess Speed . .............. 18 2.10 CosmicVelocities
    [Show full text]
  • Project Number: JMW-USC1
    Project Number: JMW-USC1 Department of Social Science and Policy Studies THE FUTURE OF UNMANNED SPACE: A SPECULATIVE ANALYSIS OF THE COMMERCIAL MARKET An Interactive Qualifying Project Report: Submitted to the Faculty of the WORCESTER POLYTECHNIC INSTITUTE in partial fulfillment of the requirements for the Degree of Bachelor of Science by ______________________________ Peter Brayshaw ______________________________ Brooks Farnham ______________________________ Jon Leslie December 16, 2004 _____________________________ ________________________________ Professor John M. Wilkes, Advisor Professor Peter Campisano, Co-Advisor Abstract: This report is one of many which deal with the unmanned space race. It is a prediction of who will have the greatest competitive advantage in the commercial market over the next 25 years, based on historical analogy. Background information on Russia, China, Japan, the United States and the European Space Agency, including the launch vehicles and launch services each provides, is covered. The new prospect of space platforms is also investigated. 2 Table of Contents Abstract: ...................................................................................................... 2 Table of Contents ......................................................................................... 3 Introduction ................................................................................................. 5 Literature Review ...................................................................................... 5 Project
    [Show full text]
  • A Hot Subdwarf-White Dwarf Super-Chandrasekhar Candidate
    A hot subdwarf–white dwarf super-Chandrasekhar candidate supernova Ia progenitor Ingrid Pelisoli1,2*, P. Neunteufel3, S. Geier1, T. Kupfer4,5, U. Heber6, A. Irrgang6, D. Schneider6, A. Bastian1, J. van Roestel7, V. Schaffenroth1, and B. N. Barlow8 1Institut fur¨ Physik und Astronomie, Universitat¨ Potsdam, Haus 28, Karl-Liebknecht-Str. 24/25, D-14476 Potsdam-Golm, Germany 2Department of Physics, University of Warwick, Coventry, CV4 7AL, UK 3Max Planck Institut fur¨ Astrophysik, Karl-Schwarzschild-Straße 1, 85748 Garching bei Munchen¨ 4Kavli Institute for Theoretical Physics, University of California, Santa Barbara, CA 93106, USA 5Texas Tech University, Department of Physics & Astronomy, Box 41051, 79409, Lubbock, TX, USA 6Dr. Karl Remeis-Observatory & ECAP, Astronomical Institute, Friedrich-Alexander University Erlangen-Nuremberg (FAU), Sternwartstr. 7, 96049 Bamberg, Germany 7Division of Physics, Mathematics and Astronomy, California Institute of Technology, Pasadena, CA 91125, USA 8Department of Physics and Astronomy, High Point University, High Point, NC 27268, USA *[email protected] ABSTRACT Supernova Ia are bright explosive events that can be used to estimate cosmological distances, allowing us to study the expansion of the Universe. They are understood to result from a thermonuclear detonation in a white dwarf that formed from the exhausted core of a star more massive than the Sun. However, the possible progenitor channels leading to an explosion are a long-standing debate, limiting the precision and accuracy of supernova Ia as distance indicators. Here we present HD 265435, a binary system with an orbital period of less than a hundred minutes, consisting of a white dwarf and a hot subdwarf — a stripped core-helium burning star.
    [Show full text]
  • Ariane-DP GB VA209 ASTRA 2F & GSAT-10.Indd
    A DUAL LAUNCH FOR DIRECT BROADCAST AND COMMUNICATIONS SERVICES Arianespace will orbit two satellites on its fifth Ariane 5 launch of the year: ASTRA 2F, which mainly provides direct-to-home (DTH) broadcast services for the Luxembourg-based operator SES, and the GSAT-10 communications satellite for the Indian Space Research Organization, ISRO. The choice of Arianespace by the world’s leading space communications operators and manufacturers is clear international recognition of the company’s excellence in launch services. Based on its proven reliability and availability, Arianespace continues to confirm its position as the world’s benchmark launch system. Ariane 5 is the only commercial satellite launcher now on the market capable of simultaneously launching two payloads and handling a complete range of missions, from launches of commercial satellites into geostationary orbit, to dedicated launches into special orbits. Arianespace and SES have developed an exceptional relationship of mutual trust over more than 20 years. ASTRA 2F will be the 36th satellite from the SES group (Euronext Paris and Luxembourg Bourse: SESG) to use an Ariane launcher. SES operates the leading direct-to-home (DTH) TV broadcast system in Europe, based on its Astra satellites, serving more than 135 million households via DTH and cable networks. Built by Astrium using a Eurostar E3000 platform, ASTRA 2F will weigh 6,000 kg at launch. Fitted with active Ku- and Ka-band transponders, ASTRA 2F will be positioned at 28.2 degrees East. It will deliver new-generation DTH TV broadcast services to Europe, the Middle East and Africa, and offers a design life of about 15 years.
    [Show full text]
  • Satellite Systems
    Chapter 18 REST-OF-WORLD (ROW) SATELLITE SYSTEMS For the longest time, space exploration was an exclusive club comprised of only two members, the United States and the Former Soviet Union. That has now changed due to a number of factors, among the more dominant being economics, advanced and improved technologies and national imperatives. Today, the number of nations with space programs has risen to over 40 and will continue to grow as the costs of spacelift and technology continue to decrease. RUSSIAN SATELLITE SYSTEMS The satellite section of the Russian In the post-Soviet era, Russia contin- space program continues to be predomi- ues its efforts to improve both its military nantly government in character, with and commercial space capabilities. most satellites dedicated either to civil/ These enhancements encompass both military applications (such as communi- orbital assets and ground-based space cations and meteorology) or exclusive support facilities. Russia has done some military missions (such as reconnaissance restructuring of its operating principles and targeting). A large portion of the regarding space. While these efforts have Russian space program is kept running by attempted not to detract from space-based launch services, boosters and launch support to military missions, economic sites, paid for by foreign commercial issues and costs have lead to a lowering companies. of Russian space-based capabilities in The most obvious change in Russian both orbital assets and ground station space activity in recent years has been the capabilities. decrease in space launches and corre- The influence of Glasnost on Russia's sponding payloads. Many of these space programs has been significant, but launches are for foreign payloads, not public announcements regarding space Russian.
    [Show full text]
  • 1. INTRODUCTION 2. EASY INSTALLATION GUIDE 8. Explain How to Download S/W by USB and How to Upload and Download 9. HOW to DOWNLO
    1. INTRODUCTION Overview…………………………………………………………………………..………………...……... 2 Main Features……………………………………………………………………………... ...………... ....4 2. EASY INSTALLATION GUIDE...…………...…………...…………...…………...……….. .. 3 3. SAFETY Instructions.………………………………………………………………………… …6 4. CHECK POINTS BEFORE USE……………………………………………………………… 7 Accessories Satellite Dish 5. CONTROLS/FUNCTIONS……………………………………………………………………….8 Front/Rear panel Remote controller Front Display 6. EQUIPMENT CONNECTION……………………………………………………………....… 11 CONNECTION WITH ANTENNA / TV SET / A/V SYSTEM 7. OPERATION…………………………………………………………………….………………….. 12 Getting Started System Settings Edit Channels EPG CAM(COMMON INTERFACE MODULE) Only CAS(CONDITIONAL ACCESS SYSTEM) USB Menu PVR Menu 8. Explain how to download S/W by USB and how to upload and download channels by USB……………………….……………………………………….…………………31 9. HOW TO DOWNLOAD SOFTWARE FROM PC TO RECEIVER…………….…32 10. Trouble Shooting……………………….……………………………………….………………34 11. Specifications…………………………………………………………………….……………….35 12. Glossary of Terms……………………………………………………………….……………...37 1 INTRODUCTION OVERVIEW This combo receiver is designed for using both free-to-air and encrypted channel reception. Enjoy the rich choice of more than 20,000 different channels, broadcasting a large range of culture, sports, cinema, news, events, etc. This receiver is a technical masterpiece, assembled with the highest qualified electronic parts. MAIN FEATURES • High Definition Tuners : DVB-S/DVB-S2 Satellite & DVB-T Terrestrial Compliant • DVB-S/DVB-S2 Satellite Compliant(MPEG-II/MPEG-IV/H.264)
    [Show full text]
  • From Strength to Strength Worldreginfo - 24C738cf-4419-4596-B904-D98a652df72b 2011 SES Astra and SES World Skies Become SES
    SES Annual report 2013 Annual Annual report 2013 From strength to strength WorldReginfo - 24c738cf-4419-4596-b904-d98a652df72b 2011 SES Astra and SES World Skies become SES 2010 2009 3rd orbital position Investment in O3b Networks over Europe 2008 2006 SES combines Americom & Coverage of 99% of New Skies into SES World Skies the world’s population 2005 2004 SES acquires New Skies Satellites Launch of HDTV 2001 Acquisition of GE Americom 1999 First Ka-Band payload in orbit 1998 Astra reaches 70m households in Europe Second orbital slot: 28.2° East 1996 SES lists on Luxembourg Stock Exchange First SES launch on Proton: ASTRA 1F Digital TV launch 1995 ASTRA 1E launch 1994 ASTRA 1D launch 1993 ASTRA 1C launch 1991 ASTRA 1B launch 1990 World’s first satellite co-location Astra reach: 16.6 million households in Europe 1989 Start of operations @ 19.2° East 1988 ASTRA 1A launches on board Ariane 4 1st satellite optimised for DTH 1987 Satellite control facility (SCF) operational 1985 SES establishes in Luxembourg Europe’s first private satellite operator WorldReginfo - 24c738cf-4419-4596-b904-d98a652df72b 2012 First emergency.lu deployment SES unveils Sat>IP 2013 SES reach: 291 million TV households worldwide SES maiden launch with SpaceX More than 6,200 TV channels 1,800 in HD 2010 First Ultra HD demo channel in HEVC 3rd orbital position over Europe 25 years in space With the very first SES satellite, ASTRA 1A, launched on December 11 1988, SES celebrated 25 years in space in 2013. Since then, the company has grown from a single satellite/one product/one-market business (direct-to-home satellite television in Europe) into a truly global operation.
    [Show full text]
  • The ASTRA Satellite System the ASTRA Satellite System at 19.2° East Services on ASTRA (September 2000)
    Société Européenne des Satellites SES in brief (I) u Operator of ASTRA, the leading DTH satellite system in Europe u Satellite fleet: è 9 satellites in operation (7 at 19.2° East, 2 at 28.2° East) è 4 additional satellites until end of year 2001 u ASTRA carries more than 600 digital and analogue TV services and 389 radio services of leading European and international broadcasters for Europe's main language markets u ASTRA audience exceeds 79 million households in 22 European countries SES in brief (II) u Company listed on Luxembourg and Frankfurt Stock Exchanges èinstitutional and private shareholders èLuxembourg State holds 16.67 % of equity è33% of capital floated on Stock Exchange u Operating under a concession agreement with the Luxembourg State u 426 employees of 20 different nations u Turnover 1999: EUR 725.2 million H1 2000: EUR 403.0 million The ASTRA Satellite System The ASTRA Satellite System at 19.2° East Services on ASTRA (September 2000) 19.2° East u 85 analogue TV services for the German, English and pan- European market u 324 digital TV services for the French, German, More than -to-air Spanish, Dutch, Polish, Italian, Luxembourgish 75 free and pan-European market TV services u 313 analogue and digital radio services 28.2° East u 207 digital TV services for the UK and Ireland u 72 digital audio services for the UK and Ireland ASTRA coverage in Europe* (Mid Year 1992 to 2000) 90 80 70 60 50 40 30 20 ASTRA Households in Mill. 10 0 1992 1993 1994 1995 1996 1997 1998 1999 2000 DTH&SMATV 9.77 13.87 16.71 21.43 22.03 23.57 25.83 27.92 29.04 Cable 26.98 31.33 36.44 37.49 41.97 44.70 47.61 49.05 50.20 *22 European countries within the ASTRA footprint Source: SES/ASTRA, Satellite Monitors SES/ASTRA, Market Information Group, August 2000 Forecast of European DTH/SMATV Households 1997 – 2010 DTH/SMATV Households in Mill.
    [Show full text]
  • Positioning: Drift Orbit and Station Acquisition
    Orbits Supplement GEOSTATIONARY ORBIT PERTURBATIONS INFLUENCE OF ASPHERICITY OF THE EARTH: The gravitational potential of the Earth is no longer µ/r, but varies with longitude. A tangential acceleration is created, depending on the longitudinal location of the satellite, with four points of stable equilibrium: two stable equilibrium points (L 75° E, 105° W) two unstable equilibrium points ( 15° W, 162° E) This tangential acceleration causes a drift of the satellite longitude. Longitudinal drift d'/dt in terms of the longitude about a point of stable equilibrium expresses as: (d/dt)2 - k cos 2 = constant Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF EARTH ASPHERICITY VARIATION IN THE LONGITUDINAL ACCELERATION OF A GEOSTATIONARY SATELLITE: Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN & MOON ATTRACTION Gravitational attraction by the sun and moon causes the satellite orbital inclination to change with time. The evolution of the inclination vector is mainly a combination of variations: period 13.66 days with 0.0035° amplitude period 182.65 days with 0.023° amplitude long term drift The long term drift is given by: -4 dix/dt = H = (-3.6 sin M) 10 ° /day -4 diy/dt = K = (23.4 +.2.7 cos M) 10 °/day where M is the moon ascending node longitude: M = 12.111 -0.052954 T (T: days from 1/1/1950) 2 2 2 2 cos d = H / (H + K ); i/t = (H + K ) Depending on time within the 18 year period of M d varies from 81.1° to 98.9° i/t varies from 0.75°/year to 0.95°/year Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN RADIATION PRESSURE Due to sun radiation pressure, eccentricity arises: EFFECT OF NON-ZERO ECCENTRICITY L = difference between longitude of geostationary satellite and geosynchronous satellite (24 hour period orbit with e0) With non-zero eccentricity the satellite track undergoes a periodic motion about the subsatellite point at perigee.
    [Show full text]
  • High Altitude Nuclear Detonations (HAND) Against Low Earth Orbit Satellites ("HALEOS")
    High Altitude Nuclear Detonations (HAND) Against Low Earth Orbit Satellites ("HALEOS") DTRA Advanced Systems and Concepts Office April 2001 1 3/23/01 SPONSOR: Defense Threat Reduction Agency - Dr. Jay Davis, Director Advanced Systems and Concepts Office - Dr. Randall S. Murch, Director BACKGROUND: The Defense Threat Reduction Agency (DTRA) was founded in 1998 to integrate and focus the capabilities of the Department of Defense (DoD) that address the weapons of mass destruction (WMD) threat. To assist the Agency in its primary mission, the Advanced Systems and Concepts Office (ASCO) develops and maintains and evolving analytical vision of necessary and sufficient capabilities to protect United States and Allied forces and citizens from WMD attack. ASCO is also charged by DoD and by the U.S. Government generally to identify gaps in these capabilities and initiate programs to fill them. It also provides support to the Threat Reduction Advisory Committee (TRAC), and its Panels, with timely, high quality research. SUPERVISING PROJECT OFFICER: Dr. John Parmentola, Chief, Advanced Operations and Systems Division, ASCO, DTRA, (703)-767-5705. The publication of this document does not indicate endorsement by the Department of Defense, nor should the contents be construed as reflecting the official position of the sponsoring agency. 1 Study Participants • DTRA/AS • RAND – John Parmentola – Peter Wilson – Thomas Killion – Roger Molander – William Durch – David Mussington – Terry Heuring – Richard Mesic – James Bonomo • DTRA/TD – Lewis Cohn • Logicon RDA – Les Palkuti – Glenn Kweder – Thomas Kennedy – Rob Mahoney – Kenneth Schwartz – Al Costantine – Balram Prasad • Mission Research Corp. – William White 2 3/23/01 2 Focus of This Briefing • Vulnerability of commercial and government-owned, unclassified satellite constellations in low earth orbit (LEO) to the effects of a high-altitude nuclear explosion.
    [Show full text]
  • Highlights in Space 2010
    International Astronautical Federation Committee on Space Research International Institute of Space Law 94 bis, Avenue de Suffren c/o CNES 94 bis, Avenue de Suffren UNITED NATIONS 75015 Paris, France 2 place Maurice Quentin 75015 Paris, France Tel: +33 1 45 67 42 60 Fax: +33 1 42 73 21 20 Tel. + 33 1 44 76 75 10 E-mail: : [email protected] E-mail: [email protected] Fax. + 33 1 44 76 74 37 URL: www.iislweb.com OFFICE FOR OUTER SPACE AFFAIRS URL: www.iafastro.com E-mail: [email protected] URL : http://cosparhq.cnes.fr Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law The United Nations Office for Outer Space Affairs is responsible for promoting international cooperation in the peaceful uses of outer space and assisting developing countries in using space science and technology. United Nations Office for Outer Space Affairs P. O. Box 500, 1400 Vienna, Austria Tel: (+43-1) 26060-4950 Fax: (+43-1) 26060-5830 E-mail: [email protected] URL: www.unoosa.org United Nations publication Printed in Austria USD 15 Sales No. E.11.I.3 ISBN 978-92-1-101236-1 ST/SPACE/57 *1180239* V.11-80239—January 2011—775 UNITED NATIONS OFFICE FOR OUTER SPACE AFFAIRS UNITED NATIONS OFFICE AT VIENNA Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law Progress in space science, technology and applications, international cooperation and space law UNITED NATIONS New York, 2011 UniTEd NationS PUblication Sales no.
    [Show full text]
  • 1998 Year in Review
    Associate Administrator for Commercial Space Transportation (AST) January 1999 COMMERCIAL SPACE TRANSPORTATION: 1998 YEAR IN REVIEW Cover Photo Credits (from left): International Launch Services (1998). Image is of the Atlas 2AS launch on June 18, 1998, from Cape Canaveral Air Station. It successfully orbited the Intelsat 805 communications satellite for Intelsat. Boeing Corporation (1998). Image is of the Delta 2 7920 launch on September 8, 1998, from Vandenberg Air Force Base. It successfully orbited five Iridium communications satellites for Iridium LLP. Lockheed Martin Corporation (1998). Image is of the Athena 2 awaiting its maiden launch on January 6, 1998, from Spaceport Florida. It successfully deployed the NASA Lunar Prospector. Orbital Sciences Corporation (1998). Image is of the Taurus 1 launch from Vandenberg Air Force Base on February 10, 1998. It successfully orbited the Geosat Follow-On 1 military remote sensing satellite for the Department of Defense, two Orbcomm satellites and the Celestis 2 funerary payload for Celestis Corporation. Orbital Sciences Corporation (1998). Image is of the Pegasus XL launch on December 5, 1998, from Vandenberg Air Force Base. It successfully orbited the Sub-millimeter Wave Astronomy Satellite for the Smithsonian Astrophysical Observatory. 1998 YEAR IN REVIEW INTRODUCTION INTRODUCTION In 1998, U.S. launch service providers conducted In addition, 1998 saw continuing demand for 22 launches licensed by the Federal Aviation launches to deploy the world’s first low Earth Administration (FAA), an increase of 29 percent orbit (LEO) communication systems. In 1998, over the 17 launches conducted in 1997. Of there were 17 commercial launches to LEO, 14 these 22, 17 were for commercial or international of which were for the Iridium, Globalstar, and customers, resulting in a 47 percent share of the Orbcomm LEO communications constellations.
    [Show full text]