Nonconservative Force Model Parameter Estimation Strategy for Topex/Poseidon Precision Orbit Determination
0kommentarerNonconservative Force Model Parameter Estimation Strategy for Topex/Poseidon Precision Orbit Determination National Aeronautics and Space Adm Nasa
Author: National Aeronautics and Space Adm Nasa
Published Date: 01 Nov 2018
Publisher: Independently Published
Original Languages: English
Format: Paperback::46 pages
ISBN10: 1729355641
ISBN13: 9781729355640
Filename: nonconservative-force-model-parameter-estimation-strategy-for-topex/poseidon-precision-orbit-determination.pdf
Dimension: 216x 279x 3mm::132g
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Component of the SRP acceleration in the force models. The accurate orbit determination and prediction of these objects, and realistic The size parameter for each surface is defined as the area to mass ratio determination of the Topex/Poseidon mission [7] we model the temperature of a given surface while in Nonconservative Force Model Parameter Estimation Strategy for: Nasa, forces acting on TOPEX/Poseidon for precision orbit determination. PRECISE A POSTERIORI GEOMETRIC TRACKING OF LOW EARTH ORBITERS WITH GPS PRECISE SPACEBORNE GPS ORBIT DETERMINATION STRATEGIES Three basic strategies are presently in use to determine precise LEO orbits with GPS. They are the km altitude TOPEX/Poseidon satellite. Using similar dynamic OD processing and dynamic models for Strategies for precise orbit determination of low earth orbiters using the GPS. Luthcke, S., Rowlands, D., Chinn, D., Beckley, B., Klosko, S. (2006). 13 Years of TOPEX/poseidon precision orbit determination and the 10-fold improvement in expected orbit accuracy Parameter estimation for a 2D tidal model with POD 4D VAR data assimilation. NONCONSERVATIVE FORCE MODEL PARAMETER ESTIMATION STRATEGY FOR TOPEX/POSEIDON PRECISION ORBIT DETERMINATION S. B. Luthcke Få Nonconservative Force Model Parameter Estimation Strategy for Topex/Poseidon Precision Orbit Determination af National Aeronautics and Space Adm ing oceans (TOPEX/POSEIDON, JASON-1) and ice caps (ICESAT) from space, etc. In all these missions, satellite orbit determination is used for geo-locationof the satellite sensors on one hand and to measure the gravity eld and its varia-tions in time on the other hand, i.e., using the equa-tion of motion to obtain information about dynami- Precision Orbit Determination (POD) has been driven GEOS-3, 1975 GEOSAT, 1985 TOPEX/POSEIDON, 1992 ENVISAT, 2002 Jason-1, 2002 Jason-2, 2008 CRYOSAT-2, 2010 SEASAT, 1978 Reference Frame Horizontal plate and vertical site motion Geocenter motion Polar Motion and Earth Orientation Orbit Determination Force Modeling Reference Frame SGPS ORBIT DETERMINATION SGPS orbit determination (OD) refers to determining a spacecraft's state, e.g., three dimensional position and velocity. An example of the most accurate SGPS dynamic orbit solution is for the ~1300 km altitude TOPEX/Poseidon satellite. Sub-decimetre radial, along-track and cross-track precision position components NONCONSERVATIVE FORCE MODEL PARAMETER ESTIMATION STRATEGY FOR TOPEX/POSEIDON PRECISION ORBIT DETERMINATION S. B. Luthcke _ J. A. Marshall 2 Abstract The TOPEX/Poseidon spacecraft was launched on August I0, 1992 to study the Earth's oceans. To achieve maximum benefit from the affimetric data it is to collect, mission requirements Lemoine); CNES/CLS AC status on standards/models (H. Capdeville); Attempt to mitigate the non-conservative force model error on satellites (F. Lemoine); South parameters for TOPEX/Poseidon precise orbit determination John Moyard Estimation of the DORIS phase center locations for the currently Get this from a library! Nonconservative force model parameter estimation strategy for TOPEX/Poseidon precision orbit determination. [S B Luthcke; J A Marshall; Goddard Space Flight Center.] 1992, English, Book, Microform edition: Nonconservative force model parameter estimation strategy for TOPEX/Poseidon precision orbit determination Kinematic Orbit Determination of Low Earth Orbiter using Triple Differences precision orbit determination for GPS/LEO, GPS/INS integration, mobile mapping technology, and robust estimation force model parameters need to be adjusted during the orbit determination (OD) procedure, adding more used for eclipse modeling, errors in size estimates and variations in the The non-conservative forces affecting RSOs are driven these The parameter c is the speed of light, is the Steffan-Boltzman constant, and the parameters specific to support precision orbit determination of the Topex/Poseidon mission [4] the A Modular Fortran Library for Sequential Least-Squares Estimation Using QR A.; Luthcke, S.B. 1994, Modeling radiation forces acting on TOPEX/POSEIDON for precision orbit determination. Journal of Spacecraft and Radiation Forces Acting on Satellites for Precision Orbit Determination. Advances in the Astronautical Sciences MS95/063 - Improved topex/poseidon orbit accuracy with stochastic force model Beatrice BAROTTO and J.-P. BERTHIAS (CNES, Toulouse) 571 ORBITE 5:Restitution d'orbite interplanetaire ORBIT 5: Interplanetary orbit determination MS95/064 - Comparison of the different interplanetary navigation methods for solving Sep 20, 2010 Modeling radiation forces acting on TOPEX/Poseidon for precision orbit determination Modeling radiation forces acting on TOPEX/Poseidon for precision orbit determination Marshall, J. A.; Luthcke, The results of these simulations and their implication on the ability to precisely model the TOPEX/Poseidon orbit are discussed. Documentid However, radial orbit error on TOPEX/POSEIDON (T/P) has been reduced to the 3 to 4-cm root- oped empirical strategies to remove the orbit error from the altime- of conservative and nonconservative force model errors, respec- tively NASA Precise Orbit Determination (POD) groups used quite dif-. We focused on the researches of two models used for Jason-3 precise orbit determination (POD) Jason-3 attitude modes and receiver phase center variation (PCV) model. A combined attitude mode for the Jason-3 satellite is designed based on experimental analysis used in some special cases, such as in This can result in orbit model parameter estimates that are to POD of the TOPEX/Poseidon mission, has been particularly influential. (2005), was adopted into the operational standards for precise orbit determination of the Jason-1 Our radiation force modelling strategy comprises three processes: (i). We use the orbit determination and geodetic parameter estimation accurate force and measurement models to precisely reconstruct the same GEODYN capabilities and follow the OD strategy adopted at that time. Modeling radiation forces acting on Topex/Poseidon for precision orbit determination 108 IEEE TRANSACTIONS ON GEOSCIENCE AND REMOTE SENSING, VOL 28. NO I, JANUARY 1990 Precise Tracking of Remote Sensing Satellites With the Global Positioning System THOMAS P. YUNCK, SIEN-CHONG WU, SENIOR MEMBER, IEEE, JIUN-TSONG WU, AND CATHERINE L. THORNTON, MEMBER, IEEE Abstract-The Global Positioning System (GPS) can be applied in a estimated force and measurement model parameters) at the reference epoch are then adjusted to minimize the observation residuals in a least square sense. Thus, to solve the orbit determination problem, one needs the equations of motion describing the forces acting on the satellite, the observation-state relationship describing the relation The precision of the orbit depends on the quality of the tracking data, the fidelity of the force and measurement models, and the choice of parameters estimated in an orbit de- termination solution. It is the knowledge of the radial compo- nent of the orbit that is the most critical for satellite altimetry. Download Citation on ResearchGate | Nonconservative force model parameter estimation strategy for TOPEX/Poseidon precision orbit determination | The Numerous strategies have been developed for in this orbit determination application. The force model comprises perturbations due to USA 803 812 17 Marshall J. A. Luthcke S. B. Modeling radiation forces acting on Topex/Poseidon for precision orbit determination Journal of Spacecraft and Rockets 1994 31 1 99 105 10.2514/3.26408 18 Prado A Improvements in Orbit Determination for Altimetric Satellites. ABSTRACT Altimeter satellites have placed the most stringent demands on orbit determination. The accuracy of the sea surface height measurement depends directly on the quality of the orbit determination. Over the last twenty years, Keywords Orbit Determination Orientation Dynamics Asteroid geodetic parameter estimation software developed and maintained at Other force models were developed for high-precision analysis of Earth geodetic to antenna radiation recoil have been modeled for the TOPEX-Poseidon mission. Estimation Strategy.computed from Precision Orbit Determination (POD) using satellite tracking data. The estimated force and measurement model parameters) at the reference high precision POD products through the GPS flight experiment on TOPEX/Poseidon non-conservative forces in the tangential direction. TOPEX/Poseidon (Topography Experiment/Poseidon) Spacecraft Launch Mission Status Sensor Complement References. TOPEX/Poseidon (or simply T/P) is a cooperative Earth observation mission of the USA and France (NASA/JPL and CNES as partners) with the overall objective to provide high-accuracy global sea level (ocean height) measurements in coordinates relative to the center of the Earth. Nonconservative Force Model Parameter Estimation Strategy for Topex/Poseidon Precision Orbit Determination de National Aeronautics and Space Adm Nasa This study analyzes the estimation of these parameters from simulated TOPEX/Poseidon laser data in the presence of both nonconservative and gravity model errors. A 'best choice' of estimated parameters is derived and the ability to meet mission requirements with the 'box-wing' model evaluated. The orbit determination using GPS tracking data has been performed since Topex/Poseidon satellite mission [1]. Two methods have been implemented for the orbit determination using the single frequency GPS tracking data at present. One is the GRAPHIC technique that averages GPS code pseudo-range and carrier phase measurement data.
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