Astronautical Glossary (C) Copyright Jonathan Mcdowell 2020 2 Chapter 1
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Alactic Observer
alactic Observer G John J. McCarthy Observatory Volume 14, No. 2 February 2021 International Space Station transit of the Moon Composite image: Marc Polansky February Astronomy Calendar and Space Exploration Almanac Bel'kovich (Long 90° E) Hercules (L) and Atlas (R) Posidonius Taurus-Littrow Six-Day-Old Moon mosaic Apollo 17 captured with an antique telescope built by John Benjamin Dancer. Dancer is credited with being the first to photograph the Moon in Tranquility Base England in February 1852 Apollo 11 Apollo 11 and 17 landing sites are visible in the images, as well as Mare Nectaris, one of the older impact basins on Mare Nectaris the Moon Altai Scarp Photos: Bill Cloutier 1 John J. McCarthy Observatory In This Issue Page Out the Window on Your Left ........................................................................3 Valentine Dome ..............................................................................................4 Rocket Trivia ..................................................................................................5 Mars Time (Landing of Perseverance) ...........................................................7 Destination: Jezero Crater ...............................................................................9 Revisiting an Exoplanet Discovery ...............................................................11 Moon Rock in the White House....................................................................13 Solar Beaming Project ..................................................................................14 -
The Lageos System
NASA TECHNICAL NASA TM X-73072 MEMORANDUM (NASA-TB-X-73072) liif LAGECS SYSTEM (NASA) E76-13179 68 p BC $4.5~ CSCI 22E Thls Informal documentation medium is used to provide accelerated or speclal release of technical information to selected users. The contents may not meet NASA formal editing and publication standards, my be re- vised, or may be incorporated in another publication. THE LAGEOS SYSTEM Joseph W< Siry NASA Headquarters Washington, D. C. 20546 NATIONAL AERONAUTICS AND SPACE ADMlNlSTRATlCN WASHINGTON, 0. C. DECEMBER 1975 1. i~~1Yp HASA TW X-73072 4. Titrd~rt. 5.RlpDltDM December 1975 m UG~SSYSEM 6.-0-cad8 . 7. A#umrtsI ahr(onninlOlyceoa -* Joseph w. Siry . to. work Uld IYa n--w- WnraCdAdbar I(ASA Headquarters Office of Applications . 11. Caoa oc <irr* 16. i+ashingtcat, D. C. 20546 12TmdRlponrrd~~ 12!3mnm&@~nsnendAddrs Technical Memorandum 1Sati-1 Aeronautics and Space Adninistxation Washington, D. C. 20546 14. sponprip ~gmcvu 15. WDPa 18. The LAGEOS system is defined and its rationale is daveloped. This report was prepared in February 1974 and served as the basis for the LAGMS Satellite Program development. Key features of the baseline system specified then included a circular orbit at 5900 km altitude and an inclination of lloO, and a satellite 60 cm in diameter weighing same 385 kg and mounting 440 retro- reflectors, each having a diameter of 3.8 cm, leaving 30% of the spherical surface available for reflecting sunlight diffusely to facilitate tracking by Baker-Nunn cameras, The satellite weight was increased to 411 kg in the actual design thr~aghthe addition of a 4th-stage apogee-kick motor. -
Lageos Orbit Decay Due to Infrared Radiation from Earth
https://ntrs.nasa.gov/search.jsp?R=19870006232 2020-03-20T12:07:45+00:00Z View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by NASA Technical Reports Server Lageos Orbit Decay Due to Infrared Radiation From Earth David Parry Rubincam JANUARY 1987 NASA Technical Memorandum 87804 Lageos Orbit Decay Due to Infrared Radiation From Earth David Parry Rubincam Goddard Space Flight Center Greenbelt, Maryland National Aeronautics and Space Administration Goddard Space Flight Center Greenbelt, Maryland 20771 1987 1 LAGEOS ORBIT DECAY r DUE TO INFRARED RADIATION FROM EARTH by David Parry Rubincam Geodynamics Branch, Code 621 NASA Goddard Space Flight Center Greenbelt, Maryland 20771 i INTRODUCTION The Lageos satellite is in a high-altitude (5900 km), almost circular orbit about the earth. The orbit is retrograde: the orbital plane is tipped by about 110 degrees to the earth’s equatorial plane. The satellite itself consists of two aluminum hemispheres bolted to a cylindrical beryllium copper core. Its outer surface is studded with laser retroreflectors. For more information about Lageos and its orbit see Smith and Dunn (1980), Johnson et al. (1976), and the Lageos special issue (Journal of Geophysical Research, 90, B 11, September 30, 1985). For a photograph see Rubincam and Weiss (1986) and a structural drawing see Cohen and Smith (1985). Note that the core is beryllium copper (Johnson et ai., 1976), and not brass as stated by Cohen and Smith (1985) and Rubincam (1982). See Table 1 of this paper for other parameters relevant to Lageos and the study presented here. -
Alactic Observer Gjohn J
alactic Observer GJohn J. McCarthy Observatory Volume 5, No. 2 February 2012 Belly of the Beast At the center of the Milky Way galaxy, a gas cloud is on a perilous journey into a supermassive black hole. As the cloud stretches and accelerates, it gives away the location of its silent predator. For more information , see page 9 inside, or go to http://www.nasa.gov/ centers/goddard/news/topstory/2008/ blackhole_slumber.html. Credit: NASA/CXC/MIT/Frederick K. Baganoff et al. The John J. McCarthy Observatory Galactic Observvvererer New Milford High School Editorial Committee 388 Danbury Road Managing Editor New Milford, CT 06776 Bill Cloutier Phone/Voice: (860) 210-4117 Production & Design Phone/Fax: (860) 354-1595 Allan Ostergren www.mccarthyobservatory.org Website Development John Gebauer JJMO Staff Marc Polansky It is through their efforts that the McCarthy Observatory has Josh Reynolds established itself as a significant educational and recreational Technical Support resource within the western Connecticut community. Bob Lambert Steve Barone Allan Ostergren Dr. Parker Moreland Colin Campbell Cecilia Page Dennis Cartolano Joe Privitera Mike Chiarella Bruno Ranchy Jeff Chodak Josh Reynolds Route Bill Cloutier Barbara Richards Charles Copple Monty Robson Randy Fender Don Ross John Gebauer Ned Sheehey Elaine Green Gene Schilling Tina Hartzell Diana Shervinskie Tom Heydenburg Katie Shusdock Phil Imbrogno Jon Wallace Bob Lambert Bob Willaum Dr. Parker Moreland Paul Woodell Amy Ziffer In This Issue THE YEAR OF THE SOLAR SYSTEM ................................ 4 SUNRISE AND SUNSET .................................................. 11 OUT THE WINDOW ON YOUR LEFT ............................... 5 ASTRONOMICAL AND HISTORICAL EVENTS ...................... 11 FRA MAURA ................................................................ 5 REFERENCES ON DISTANCES ....................................... -
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. -
The Evolution of Earth Gravitational Models Used in Astrodynamics
JEROME R. VETTER THE EVOLUTION OF EARTH GRAVITATIONAL MODELS USED IN ASTRODYNAMICS Earth gravitational models derived from the earliest ground-based tracking systems used for Sputnik and the Transit Navy Navigation Satellite System have evolved to models that use data from the Joint United States-French Ocean Topography Experiment Satellite (Topex/Poseidon) and the Global Positioning System of satellites. This article summarizes the history of the tracking and instrumentation systems used, discusses the limitations and constraints of these systems, and reviews past and current techniques for estimating gravity and processing large batches of diverse data types. Current models continue to be improved; the latest model improvements and plans for future systems are discussed. Contemporary gravitational models used within the astrodynamics community are described, and their performance is compared numerically. The use of these models for solid Earth geophysics, space geophysics, oceanography, geology, and related Earth science disciplines becomes particularly attractive as the statistical confidence of the models improves and as the models are validated over certain spatial resolutions of the geodetic spectrum. INTRODUCTION Before the development of satellite technology, the Earth orbit. Of these, five were still orbiting the Earth techniques used to observe the Earth's gravitational field when the satellites of the Transit Navy Navigational Sat were restricted to terrestrial gravimetry. Measurements of ellite System (NNSS) were launched starting in 1960. The gravity were adequate only over sparse areas of the Sputniks were all launched into near-critical orbit incli world. Moreover, because gravity profiles over the nations of about 65°. (The critical inclination is defined oceans were inadequate, the gravity field could not be as that inclination, 1= 63 °26', where gravitational pertur meaningfully estimated. -
Itu Recommendation Itu-R S.1003.2
SPACE DEBRIS MITIGATION STANDARDS ITU RECOMMENDATION ITU‐R S.1003.2 International mechanism: International Telecommunications Union (ITU) Recommendation ITU‐R S.1003.2 (12/2010) Environmental protection of the geostationary‐satellite orbit Description: ITU‐R S.1003.2 provides guidance about disposal orbits for satellites in the geostationary‐ satellite orbit (GSO). In this orbit, there is an increase in debris due to fragments resulting from increased numbers of satellites and their associated launches. Given the current limitations (primarily specific impulse) of space propulsion systems, it is impractical to retrieve objects from GSO altitudes or to return them to Earth at the end of their operational life. A protected region must therefore be established above, below and around the GSO which defines the nominal orbital regime within which operational satellites will reside and manoeuvre. To avoid an accumulation of non‐functional objects in this region, and the associated increase in population density and potential collision risk that this would lead to, satellites should be manoeuvred out of this region at the end of their operational life. In order to ensure that these objects do not present a collision hazard to satellites being injected into GSO, they should be manoeuvred to altitudes higher than the GSO region, rather than lower. The recommendations embodied in ITU‐R S.1003.2 are: – Recommendation 1: As little debris as possible should be released into the GSO region during the placement of a satellite in orbit. – Recommendation 2: Every reasonable effort should be made to shorten the lifetime of debris in elliptical transfer orbits with the apogees at or near GSO altitude. -
Classification of Geosynchronous Objects
esoc European Space Operations Centre Robert-Bosch-Strasse 5 D-64293 Darmstadt Germany T +49 (0)6151 900 www.esa.int CLASSIFICATION OF GEOSYNCHRONOUS OBJECTS Produced with the DISCOS Database Prepared by ESA’s Space Debris Office Reference GEN-DB-LOG-00211-OPS-GR Issue 20 Revision 0 Date of Issue 28 May 2018 Status Issued Document Type Technical Note Distribution ESA UNCLASSIFIED - Limited Distribution European Space Agency Agence spatiale europeenne´ Abstract This is a status report on geosynchronous objects as of 1 January 2018. Based on orbital data in ESA’s DISCOS database and on orbital data provided by KIAM the situation near the geostationary ring is analysed. From 1523 objects for which orbital data are available (of which 0 are outdated, i.e. the last available state dates back to 180 or more days before the reference date), 519 are actively controlled, 795 are drifting above, below or through GEO, 189 are in a libration orbit and 19 are in a highly inclined orbit. For 1 object the status could not be determined. Furthermore, there are 59 uncontrolled objects without orbital data (of which 54 have not been cata- logued). Thus the total number of known objects in the geostationary region is 1582. If you detect any error or if you have any comment or question please contact: Stijn Lemmens European Space Agency European Space Operations Center Space Debris Office (OPS-GR) Robert-Bosch-Str. 5 64293 Darmstadt, Germany Tel.: +49-6151-902634 E-mail: [email protected] Page 1 / 187 European Space Agency CLASSIFICATION OF GEOSYNCHRONOUS OBJECTS Agence spatiale europeenne´ Date 28 May 2018 Issue 20 Rev 0 Table of contents 1 Introduction 3 2 Sources 4 2.1 USSTRATCOM Two-Line Elements (TLEs) . -
Recommendation Itu-R S.1003-2*
Recommendation ITU-R S.1003-2 (12/2010) Environmental protection of the geostationary-satellite orbit S Series Fixed-satellite service ii Rec. ITU-R S.1003-2 Foreword The role of the Radiocommunication Sector is to ensure the rational, equitable, efficient and economical use of the radio-frequency spectrum by all radiocommunication services, including satellite services, and carry out studies without limit of frequency range on the basis of which Recommendations are adopted. The regulatory and policy functions of the Radiocommunication Sector are performed by World and Regional Radiocommunication Conferences and Radiocommunication Assemblies supported by Study Groups. Policy on Intellectual Property Right (IPR) ITU-R policy on IPR is described in the Common Patent Policy for ITU-T/ITU-R/ISO/IEC referenced in Annex 1 of Resolution ITU-R 1. Forms to be used for the submission of patent statements and licensing declarations by patent holders are available from http://www.itu.int/ITU-R/go/patents/en where the Guidelines for Implementation of the Common Patent Policy for ITU-T/ITU-R/ISO/IEC and the ITU-R patent information database can also be found. Series of ITU-R Recommendations (Also available online at http://www.itu.int/publ/R-REC/en) Series Title BO Satellite delivery BR Recording for production, archival and play-out; film for television BS Broadcasting service (sound) BT Broadcasting service (television) F Fixed service M Mobile, radiodetermination, amateur and related satellite services P Radiowave propagation RA Radio astronomy RS Remote sensing systems S Fixed-satellite service SA Space applications and meteorology SF Frequency sharing and coordination between fixed-satellite and fixed service systems SM Spectrum management SNG Satellite news gathering TF Time signals and frequency standards emissions V Vocabulary and related subjects Note: This ITU-R Recommendation was approved in English under the procedure detailed in Resolution ITU-R 1. -
Deep Space Chronicle Deep Space Chronicle: a Chronology of Deep Space and Planetary Probes, 1958–2000 | Asifa
dsc_cover (Converted)-1 8/6/02 10:33 AM Page 1 Deep Space Chronicle Deep Space Chronicle: A Chronology ofDeep Space and Planetary Probes, 1958–2000 |Asif A.Siddiqi National Aeronautics and Space Administration NASA SP-2002-4524 A Chronology of Deep Space and Planetary Probes 1958–2000 Asif A. Siddiqi NASA SP-2002-4524 Monographs in Aerospace History Number 24 dsc_cover (Converted)-1 8/6/02 10:33 AM Page 2 Cover photo: A montage of planetary images taken by Mariner 10, the Mars Global Surveyor Orbiter, Voyager 1, and Voyager 2, all managed by the Jet Propulsion Laboratory in Pasadena, California. Included (from top to bottom) are images of Mercury, Venus, Earth (and Moon), Mars, Jupiter, Saturn, Uranus, and Neptune. The inner planets (Mercury, Venus, Earth and its Moon, and Mars) and the outer planets (Jupiter, Saturn, Uranus, and Neptune) are roughly to scale to each other. NASA SP-2002-4524 Deep Space Chronicle A Chronology of Deep Space and Planetary Probes 1958–2000 ASIF A. SIDDIQI Monographs in Aerospace History Number 24 June 2002 National Aeronautics and Space Administration Office of External Relations NASA History Office Washington, DC 20546-0001 Library of Congress Cataloging-in-Publication Data Siddiqi, Asif A., 1966 Deep space chronicle: a chronology of deep space and planetary probes, 1958-2000 / by Asif A. Siddiqi. p.cm. – (Monographs in aerospace history; no. 24) (NASA SP; 2002-4524) Includes bibliographical references and index. 1. Space flight—History—20th century. I. Title. II. Series. III. NASA SP; 4524 TL 790.S53 2002 629.4’1’0904—dc21 2001044012 Table of Contents Foreword by Roger D. -
Horisont STIIHILINE SUURLIN NADE KASVAMINE SÜ VENDAB NENDE PUU DUSI
MH Ш/Шл Jr ffl H^H K s Horisont STIIHILINE SUURLIN NADE KASVAMINE SÜ VENDAB NENDE PUU DUSI. Nikolai Ullas, professor, Lenini preemia BftjMHfi1 laureaat #Диии . Mind aga võlub Unn. Ta rühk, щй&е ta tahm, ta tuled . ENN VETEMAA, «Apoteoos sünnilinnale». Õn traagiline, et meie linnad peavad esmajärje korras majutama autosid, — nii seisvaid kui liiku vaid. DOXIADIS, kreeka arhitekt SS- I Л ** . ж 1Ш Esikaan ja esikaane sisekülg HEINO KERSNALT. EESTI NSV ÜHINGU,,TEADU S" POPULAARTEADUSLIK AJAKIRI m ASUTATUD 196 7. A. ® ILMUB ÜKS KORD KUUS® EKP KESKKOMITEE KIRJASTUS, TALLINN Horisont. NR. 8 AUGUST 1969 Läbi sajandite ideaalse poole RAIMO PULLAT 2 * * * sajandil MALLE MEELAK 3 Linn areneb LEONID VOLKOV 24 Kümmekonna aasta pärast RENE PALIS 32 Kuidas linlane puhkab ASTA PALM 40 Tallinn muudab ilmet MART PORT 42 Molekuli saladuste jälil INTERVJUU 54 Ära hüüa hunti! FARLEY MO WAT 57 Aju ja masin KIRILL MASSAJEV 69 Enne kui filmida ARTUR RÄTSEP 72 LÄBI SAJANDITE IDEAALSE POOLE RAIMO PULLAT, ajalookandidaat Inimkonna ajalugu tunneb lugema tohutud inimhulgad. Kapitalismi tingi tuid linnu — linnu, mis õn hävinud, ja mustes süveneb vastuolu linna ja maa teisi, mis püsivad tänapäevani. Mee vahel. Kapitalistlik linn ekspluateerib nutagem tähtsaid tsivilisatsioonikeskusi: küla. Linna ja küla antagonismi kaota esimesel aastatuhandel enne mele aja mist igatsesid paljud mineviku mõtle arvamist Babülon, siis Rtolemaiose jad. Täiuslikust linnaühiskonnast unista Aleksandria ja Justinianuse Bütsants, sid juba Platon ja Aristoteles. Sadu aas Rjurikute Kiiev ja kuulus kaubalinn taid tagasi vaidlesid ideaalse linna üle Novgorod, Elizabethi-aegne London, Thomas More, Tommaso Campanella jt. Medicite Firenze, Neevalinn Peter Citta ideale kontseptsiooni leiame kä buri, suurlinnad New Yorkr Chicago, 16. -
Rendezvous and Proximity Operations: Friend Or Foe?
Promoting Cooperative Solutions for Space Sustainability Rendezvous and Proximity Operations: Friend or Foe? Victoria Samson, Washington Office Director Secure World Foundation “Supporting Diplomacy: Clearing the Path for Dialogue” UNIDIR Geneva, Switzerland May 28-29, 2019 ©2019 Secure World Foundation. Used with Permission www.swfound.org UNIDIR May 29 ,2019 @SWFoundation Development of OOS and RPO Capabilities Promoting Cooperative Solutions for Space Sustainability • On-orbit servicing (OOS) and rendezvous and proximity operations (RPO) are key to enabling future of on-orbit activities • Benefits and challenges – Greatly increase the viability of and benefits from space activities – Raises a number of diplomatic, legal, safety, operational, and policy challenges that need to be tackled • OOS and RPO are not new, and are already international – 50+ years of experience in doing it with human spaceflight, but increasingly shifting to robotic/autonomous – Multiple countries/companies developing and testing RPO capabilities • How to develop norms and standards to enable cooperative OOS/RPO and mitigate challenges? UNIDIR May 29, 2019 2 www.swfound.org @SWFoundation RPO Activities and Counterspace Objectives Promoting Cooperative Solutions for Space Sustainability • Global Counterspace Capabilities: An Open Source Assessment, April 2019 – www.swfound.org/counterspace – Compiles and assesses publicly available information on the counterspace capabilities being developed by multiple countries across five categories: direct-ascent, co-orbital,