Quality of Orbit Predictions for Satellites Tracked by SLR Stations
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
International Laser Ranging Service (ILRS)
The International Laser Ranging Service (ILRS) http://ilrs.gsfc.nasa.gov/ Chairman of the Governing Board: G. Appleby (Great Britain) Director of the Central Bureau: M. Pearlman (USA) Secretary: C. Noll (USA) Analysis Coordinator: E. C. Pavlis (USA) Development ranging and ranging to the Lunar Orbiter, with plans to extend ranging to interplanetary missions with optical Satellite Laser Ranging (SLR) was established in the mid- transponders. 1960s, with early ground system developments by NASA and CNES. Early US and French satellites provided laser Mission targets that were used mainly for inter-comparison with other tracking systems, refinement of orbit determination The ILRS collects, merges, analyzes, archives and techniques, and as input to the development of ground distributes Satellite Laser Ranging (SLR) and Lunar Laser station fiducial networks and global gravity field models. Ranging (LLR) observation data sets of sufficient accuracy Early SLR brought the results of orbit determination and to satisfy the GGOS objectives of a wide range of station positions to the meter level of accuracy. The SLR scientific, engineering, and operational applications and network was expanded in the 1970s and 1980s as other experimentation. The basic observable is the precise time- groups built and deployed systems and technological of-flight of an ultra-short laser pulse to and from a improvements began the evolution toward the decimeter retroreflector-equipped satellite. These data sets are used and centimeter accuracy. Since 1976, the main geodetic by the ILRS to generate a number of fundamental added target has been LAGEOS (subsequently joined by value products, including but not limited to: LAGEOS-2 in 1992), providing the backbone of the SLR • Centimeter accuracy satellite ephemerides technique’s contribution to the realization of the • Earth orientation parameters (polar motion and length of day) International Terrestrial Reference Frame (ITRF). -
Orbit Determination Methods and Techniques
PROJECTE FINAL DE CARRERA (PFC) GEOSAR Mission: Orbit Determination Methods and Techniques Marc Fernàndez Uson PFC Advisor: Prof. Antoni Broquetas Ibars May 2016 PROJECTE FINAL DE CARRERA (PFC) GEOSAR Mission: Orbit Determination Methods and Techniques Marc Fernàndez Uson ABSTRACT ABSTRACT Multiple applications such as land stability control, natural risks prevention or accurate numerical weather prediction models from water vapour atmospheric mapping would substantially benefit from permanent radar monitoring given their fast evolution is not observable with present Low Earth Orbit based systems. In order to overcome this drawback, GEOstationary Synthetic Aperture Radar missions (GEOSAR) are presently being studied. GEOSAR missions are based on operating a radar payload hosted by a communication satellite in a geostationary orbit. Due to orbital perturbations, the satellite does not follow a perfectly circular orbit, but has a slight eccentricity and inclination that can be used to form the synthetic aperture required to obtain images. Several sources affect the along-track phase history in GEOSAR missions causing unwanted fluctuations which may result in image defocusing. The main expected contributors to azimuth phase noise are orbit determination errors, radar carrier frequency drifts, the Atmospheric Phase Screen (APS), and satellite attitude instabilities and structural vibration. In order to obtain an accurate image of the scene after SAR processing, the range history of every point of the scene must be known. This fact requires a high precision orbit modeling and the use of suitable techniques for atmospheric phase screen compensation, which are well beyond the usual orbit determination requirement of satellites in GEO orbits. The other influencing factors like oscillator drift and attitude instability, vibration, etc., must be controlled or compensated. -
SPACE RESEARCH in POLAND Report to COMMITTEE
SPACE RESEARCH IN POLAND Report to COMMITTEE ON SPACE RESEARCH (COSPAR) 2020 Space Research Centre Polish Academy of Sciences and The Committee on Space and Satellite Research PAS Report to COMMITTEE ON SPACE RESEARCH (COSPAR) ISBN 978-83-89439-04-8 First edition © Copyright by Space Research Centre Polish Academy of Sciences and The Committee on Space and Satellite Research PAS Warsaw, 2020 Editor: Iwona Stanisławska, Aneta Popowska Report to COSPAR 2020 1 SATELLITE GEODESY Space Research in Poland 3 1. SATELLITE GEODESY Compiled by Mariusz Figurski, Grzegorz Nykiel, Paweł Wielgosz, and Anna Krypiak-Gregorczyk Introduction This part of the Polish National Report concerns research on Satellite Geodesy performed in Poland from 2018 to 2020. The activity of the Polish institutions in the field of satellite geodesy and navigation are focused on the several main fields: • global and regional GPS and SLR measurements in the frame of International GNSS Service (IGS), International Laser Ranging Service (ILRS), International Earth Rotation and Reference Systems Service (IERS), European Reference Frame Permanent Network (EPN), • Polish geodetic permanent network – ASG-EUPOS, • modeling of ionosphere and troposphere, • practical utilization of satellite methods in local geodetic applications, • geodynamic study, • metrological control of Global Navigation Satellite System (GNSS) equipment, • use of gravimetric satellite missions, • application of GNSS in overland, maritime and air navigation, • multi-GNSS application in geodetic studies. Report -
Geodesy in the 21St Century
Eos, Vol. 90, No. 18, 5 May 2009 VOLUME 90 NUMBER 18 5 MAY 2009 EOS, TRANSACTIONS, AMERICAN GEOPHYSICAL UNION PAGES 153–164 geophysical discoveries, the basic under- Geodesy in the 21st Century standing of earthquake mechanics known as the “elastic rebound theory” [Reid, 1910], PAGES 153–155 Geodesy and the Space Era was established by analyzing geodetic mea- surements before and after the 1906 San From flat Earth, to round Earth, to a rough Geodesy, like many scientific fields, is Francisco earthquakes. and oblate Earth, people’s understanding of technology driven. Over the centuries, it In 1957, the Soviet Union launched the the shape of our planet and its landscapes has developed as an engineering discipline artificial satellite Sputnik, ushering the world has changed dramatically over the course because of its practical applications. By the into the space era. During the first 5 decades of history. These advances in geodesy— early 1900s, scientists and cartographers of the space era, space geodetic technolo- the study of Earth’s size, shape, orientation, began to use triangulation and leveling mea- gies developed rapidly. The idea behind and gravitational field, and the variations surements to record surface deformation space geodetic measurements is simple: Dis- of these quantities over time—developed associated with earthquakes and volcanoes. tance or phase measurements conducted because of humans’ curiosity about the For example, one of the most important between Earth’s surface and objects in Earth and because of geodesy’s application to navigation, surveying, and mapping, all of which were very practical areas that ben- efited society. -
Solar Radiation Pressure Models for Beidou-3 I2-S Satellite: Comparison and Augmentation
remote sensing Article Solar Radiation Pressure Models for BeiDou-3 I2-S Satellite: Comparison and Augmentation Chen Wang 1, Jing Guo 1,2 ID , Qile Zhao 1,3,* and Jingnan Liu 1,3 1 GNSS Research Center, Wuhan University, 129 Luoyu Road, Wuhan 430079, China; [email protected] (C.W.); [email protected] (J.G.); [email protected] (J.L.) 2 School of Engineering, Newcastle University, Newcastle upon Tyne NE1 7RU, UK 3 Collaborative Innovation Center of Geospatial Technology, Wuhan University, 129 Luoyu Road, Wuhan 430079, China * Correspondence: [email protected]; Tel.: +86-027-6877-7227 Received: 22 December 2017; Accepted: 15 January 2018; Published: 16 January 2018 Abstract: As one of the most essential modeling aspects for precise orbit determination, solar radiation pressure (SRP) is the largest non-gravitational force acting on a navigation satellite. This study focuses on SRP modeling of the BeiDou-3 experimental satellite I2-S (PRN C32), for which an obvious modeling deficiency that is related to SRP was formerly identified. The satellite laser ranging (SLR) validation demonstrated that the orbit of BeiDou-3 I2-S determined with empirical 5-parameter Extended CODE (Center for Orbit Determination in Europe) Orbit Model (ECOM1) has the sun elongation angle (# angle) dependent systematic error, as well as a bias of approximately −16.9 cm. Similar performance has been identified for European Galileo and Japanese QZSS Michibiki satellite as well, and can be reduced with the extended ECOM model (ECOM2), or by using the a priori SRP model to augment ECOM1. In this study, the performances of the widely used SRP models for GNSS (Global Navigation Satellite System) satellites, i.e., ECOM1, ECOM2, and adjustable box-wing model have been compared and analyzed for BeiDou-3 I2-S satellite. -
Space Geodesy and Satellite Laser Ranging
Space Geodesy and Satellite Laser Ranging Michael Pearlman* Harvard-Smithsonian Center for Astrophysics Cambridge, MA USA *with a very extensive use of charts and inputs provided by many other people Causes for Crustal Motions and Variations in Earth Orientation Dynamics of crust and mantle Ocean Loading Volcanoes Post Glacial Rebound Plate Tectonics Atmospheric Loading Mantle Convection Core/Mantle Dynamics Mass transport phenomena in the upper layers of the Earth Temporal and spatial resolution of mass transport phenomena secular / decadal post -glacial glaciers polar ice post-glacial reboundrebound ocean mass flux interanaual atmosphere seasonal timetime scale scale sub --seasonal hydrology: surface and ground water, snow, ice diurnal semidiurnal coastal tides solid earth and ocean tides 1km 10km 100km 1000km 10000km resolution Temporal and spatial resolution of oceanographic features 10000J10000 y bathymetric global 1000J1000 y structures warming 100100J y basin scale variability 1010J y El Nino Rossby- 11J y waves seasonal cycle eddies timetime scale scale 11M m mesoscale and and shorter scale fronts physical- barotropic 11W w biological variability interaction Coastal upwelling 11T d surface tides internal waves internal tides and inertial motions 11h h 10m 100m 1km 10km 100km 1000km 10000km 100000km resolution Continental hydrology Ice mass balance and sea level Satellite gravity and altimeter mission products help determine mass transport and mass distribution in a multi-disciplinary environment Gravity field missions Oceanic -
Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling
Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling by Zachary James Folcik B.S. Computer Science Michigan Technological University, 2000 SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE IN AERONAUTICS AND ASTRONAUTICS AT THE MASSACHUSETTS INSTITUTE OF TECHNOLOGY JUNE 2008 © 2008 Massachusetts Institute of Technology. All rights reserved. Signature of Author:_______________________________________________________ Department of Aeronautics and Astronautics May 23, 2008 Certified by:_____________________________________________________________ Dr. Paul J. Cefola Lecturer, Department of Aeronautics and Astronautics Thesis Supervisor Certified by:_____________________________________________________________ Professor Jonathan P. How Professor, Department of Aeronautics and Astronautics Thesis Advisor Accepted by:_____________________________________________________________ Professor David L. Darmofal Associate Department Head Chair, Committee on Graduate Students 1 [This page intentionally left blank.] 2 Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling by Zachary James Folcik Submitted to the Department of Aeronautics and Astronautics on May 23, 2008 in Partial Fulfillment of the Requirements for the Degree of Master of Science in Aeronautics and Astronautics ABSTRACT The development of electric propulsion technology for spacecraft has led to reduced costs and longer lifespans for certain -
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. -
GPS Applications in Space
Space Situational Awareness 2015: GPS Applications in Space James J. Miller, Deputy Director Policy & Strategic Communications Division May 13, 2015 GPS Extends the Reach of NASA Networks to Enable New Space Ops, Science, and Exploration Apps GPS Relative Navigation is used for Rendezvous to ISS GPS PNT Services Enable: • Attitude Determination: Use of GPS enables some missions to meet their attitude determination requirements, such as ISS • Real-time On-Board Navigation: Enables new methods of spaceflight ops such as rendezvous & docking, station- keeping, precision formation flying, and GEO satellite servicing • Earth Sciences: GPS used as a remote sensing tool supports atmospheric and ionospheric sciences, geodesy, and geodynamics -- from monitoring sea levels and ice melt to measuring the gravity field ESA ATV 1st mission JAXA’s HTV 1st mission Commercial Cargo Resupply to ISS in 2008 to ISS in 2009 (Space-X & Cygnus), 2012+ 2 Growing GPS Uses in Space: Space Operations & Science • NASA strategic navigation requirements for science and 20-Year Worldwide Space Mission space ops continue to grow, especially as higher Projections by Orbit Type* precisions are needed for more complex operations in all space domains 1% 5% Low Earth Orbit • Nearly 60%* of projected worldwide space missions 27% Medium Earth Orbit over the next 20 years will operate in LEO 59% GeoSynchronous Orbit – That is, inside the Terrestrial Service Volume (TSV) 8% Highly Elliptical Orbit Cislunar / Interplanetary • An additional 35%* of these space missions that will operate at higher altitudes will remain at or below GEO – That is, inside the GPS/GNSS Space Service Volume (SSV) Highly Elliptical Orbits**: • In summary, approximately 95% of projected Example: NASA MMS 4- worldwide space missions over the next 20 years will satellite constellation. -
Assessment of Earth Gravity Field Models in the Medium to High Frequency Spectrum Based on GRACE and GOCE Dynamic Orbit Analysis
Article Assessment of Earth Gravity Field Models in the Medium to High Frequency Spectrum Based on GRACE and GOCE Dynamic Orbit Analysis Thomas D. Papanikolaou 1,2,* and Dimitrios Tsoulis 3 1 Geoscience Australia, Cnr Jerrabomberra Ave and Hindmarsh Drive, Symonston, ACT 2609, Australia 2 Cooperative Research Centre for Spatial Information, Docklands, VIC 3008, Australia 3 Department of Geodesy and Surveying, Aristotle University of Thessaloniki, 54124 Thessaloniki, Greece; [email protected] * Correspondence: [email protected] Received: 22 October 2018; Accepted: 23 November 2018; Published: 27 November 2018 Abstract: An analysis of current static and time-variable gravity field models is presented focusing on the medium to high frequencies of the geopotential as expressed by the spherical harmonic coefficients. A validation scheme of the gravity field models is implemented based on dynamic orbit determination that is applied in a degree-wise cumulative sense of the individual spherical harmonics. The approach is applied to real data of the Gravity Field and Steady-State Ocean Circulation (GOCE) and Gravity Recovery and Climate Experiment (GRACE) satellite missions, as well as to GRACE inter-satellite K-band ranging (KBR) data. Since the proposed scheme aims at capturing gravitational discrepancies, we consider a few deterministic empirical parameters in order to avoid absorbing part of the gravity signal that may be included in the monitored orbit residuals. The present contribution aims at a band-limited analysis for identifying characteristic degree ranges and thresholds of the various GRACE- and GOCE-based gravity field models. The degree range 100–180 is investigated based on the degree-wise cumulative approach. -
NASA Process for Limiting Orbital Debris
NASA-HANDBOOK NASA HANDBOOK 8719.14 National Aeronautics and Space Administration Approved: 2008-07-30 Washington, DC 20546 Expiration Date: 2013-07-30 HANDBOOK FOR LIMITING ORBITAL DEBRIS Measurement System Identification: Metric APPROVED FOR PUBLIC RELEASE – DISTRIBUTION IS UNLIMITED NASA-Handbook 8719.14 This page intentionally left blank. Page 2 of 174 NASA-Handbook 8719.14 DOCUMENT HISTORY LOG Status Document Approval Date Description Revision Baseline 2008-07-30 Initial Release Page 3 of 174 NASA-Handbook 8719.14 This page intentionally left blank. Page 4 of 174 NASA-Handbook 8719.14 This page intentionally left blank. Page 6 of 174 NASA-Handbook 8719.14 TABLE OF CONTENTS 1 SCOPE...........................................................................................................................13 1.1 Purpose................................................................................................................................ 13 1.2 Applicability ....................................................................................................................... 13 2 APPLICABLE AND REFERENCE DOCUMENTS................................................14 3 ACRONYMS AND DEFINITIONS ...........................................................................15 3.1 Acronyms............................................................................................................................ 15 3.2 Definitions .........................................................................................................................