Results 261 to 270 of about 6,687 (290)

HY-2D input data for Precise Orbit Determination

2021
This document describes the information required to ensure optimal parameterisation of on-board and ground POD processing software in the HY-2D context.
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A precise determination of the 3s proton orbit

Nuclear Physics A, 1983
Abstract Elastic electron scattering cross sections have been measured for 205 Tl and 206 Pb at an incident energy of 502 MeV, covering a momentum transfer range from 1.4 to 3.2 fm −1 . The charge density difference of the two isotones is accurately determined.
B. Frois, J.M. Cavedon, D. Goutte, M. Huet, Ph. Leconte, C.N. Papanicolas, X.-H. Phan, S.K. Platchkov, S.E. Williamson, W. Boeglin, I. Sick   +10 more
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Thermospheric events in CHAMP Precise Orbit Determination

2003
The accelerometer on-board the CHAMP satellite measures thermospheric events like large solar mass eruptions reaching Earth. The accelerometer data allow to replace the models for the non-conservative forces in Precise Orbit Determination (POD). The paper will discuss the impacts on POD and show some of the results.
König, R., Neumayer, K.
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The EUMETSAT Environment for Precise Orbit Determination

SpaceOps 2008 Conference, 2008
In the frame of the processing of data from the GNSS Receiver for Atmospheric Sounding (GRAS) instrument onboard the MetOp satellites, EUMETSAT has developed an environment for operational Precise Orbit Determination (POD) processing and validation. The design of this POD environment, in which several components for validation, monitoring, reprocessing
Yago Andrés, Francisco Sancho, Christian Marquardt   +2 more
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Problem of algorithm in precision orbit determination

Science in China Series A: Mathematics, 1999
In orbit determination, the precision ephemeris and state transition matrix are usually obtained by solving two groups of ordinary differential equations with numerical integration method due to the complexity of the force models. A kind of simplified analytical method to compute the state transition matrix is given.
Lin Liu, Qiang Zhang, Xinhao Liao
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Precision orbit determination for TOPEX/POSEIDON

Journal of Geophysical Research: Oceans, 1994
The TOPEX/POSEIDON mission objective requires that the radial position of the spacecraft be determined with an accuracy better than 13 cm RMS (root mean square). This stringent requirement is an order of magnitude below the accuracy achieved for any altimeter mission prior to the definition of the TOPEX/POSEIDON mission.
B. D. Tapley, J. C. Ries, G. W. Davis, R. J. Eanes, B. E. Schutz, C. K. Shum, M. M. Watkins, J. A. Marshall, R. S. Nerem, B. H. Putney, S. M. Klosko, S. B. Luthcke, D. Pavlis, R. G. Williamson, N. P. Zelensky   +14 more
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Precise orbit determination for CAPS project

2010 5th ESA Workshop on Satellite Navigation Technologies and European Workshop on GNSS Signals and Signal Processing (NAVITEC), 2010
The Chinese Area Positioning System (CAPS) is a new type of satellite navigation systems. The geostationary satellites for normal communication with 2 or 3 sets of inclined geostationary orbit (GEO) satellites are employed to construct a satellite navigation system.
Wu Wenjun, Li Zhigang, Chen Xuan, Lei Hui, Yang Xuhai, Feng Chugang   +5 more
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Approaches to CHAMP precise orbit determination

2003
With a tailored gravity field model, the dynamic restitution of the CHAMP orbit can be carried out quite accurately. The solution can be based on the onboard accelerometer data or on dynamical models with additional parameters. Beside the dynamic mode, also a geometric/kinematic satellite position determination is implemented in the GFZ POD software ...
Neumayer, K., König, R., Zhu, S.
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I: PRECISE ORBIT DETERMINATION AND GRAVITY FIELD MODELLING: Strategies for Precise Orbit Determination of Low Earth Orbiters Using the GPS

Space Science Reviews, 2003
Considerable experience accumulated during the past decade in strategies for processing GPS data from ground-based geodetic receivers. First experience on the use of GPS observations from spaceborne receivers for orbit determination of satellites on low altitude orbits was gained with the launch of TOPEX/POSEIDON ten years ago.
U. Hugentobler, G. Beutler
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Effect of GPS orbit errors on ICESat precision orbit determination

Astrodynamics Specialist Conference, 2000
To achieve the orbit determination requirement of the EOS ICESat, which is 5 cm and 20 cm in radial and horizontal components, respectively, using the GPS tracking system, it is required to use the precise GPS ephemeris. Three different levels of GPS orbit errors were generated through a simulation, and the effect of these GPS orbit errors on ICESat ...
H. Rim, C. Webb, B. Schutz
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