Estimation of Earth orientation parameters in the problem of coordinate-time supporting for navigation satellites

Mathematics. Physics. Mechanics


Аuthors

Vu Viet Trung

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

e-mail: vuviettrung@yandex.ru

Abstract

Development and modeling algorithm to compute the ephemeris prediction, which accounting the Earth rotation parameters in the problem of coordinate-time supporting for navigation satellites.
In order to improve the accuracy of navigation tasks was developed algorithm with the Earth rotation parameters, which are in the differential equations of the orbital motion of the satellite and the matrix of transition from terrestrial to celestial coordinate system and vice versa.
Theoretical modeling of the vibrational-rotational motion of the deformable Earth, appropriate observations and measurements are carried out by using the approximate methods of nonlinear mechanics, combining with numerical experiment. Oscillating process is described by model of the Earth’s pole, which is based on the considering gravitational-tidal torques from the Sun and the Moon. In implementing the transition from terrestrial to celestial coordinate system has been used numerical methods of the celestial mechanics for the calculation precession and nutation parameters, which are recommended by the International Astronomical Union (IAU).
Modeling the orbital motion of the navigation satellites was simulated on the basis of the constructed algorithm in inside revolution time interval within the models of Earth’s rotation parameters, which are adequate observations and measurements IERS and accepted theory of nutation IAU. The results of modeling is shown that the mathematical models used EOP (Earth's poles oscillating process and irregular rotation of the Earth) and the developed algorithms with their directly accounting on the basis of IERS, to extend the time interval and increase the prediction accuracy of the satellite ephemeris.
The developed algorithm for computing the prediction ephemeris within the Earth rotation parameters can be applied to solve the problems of coordinate-time supporting for navigation satellite and other tasks that associated with the movement of the satellites in medium and geostationary orbits. The implementation of the transition from terrestrial to celestial coordinate system with the forecasting ability not only solves the problems, which are associated with the orbital motion of the satellite, but also series of important geophysical, geodetic, astronomical and other tasks.

Keywords:

earth’s pole, universal time, preccesion, nutation, navigation satellite, celestial coordinate system, terrestrial coordinate system

References

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