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A Combined Numerical-Empirical Orbit Propagation Algorithm for Satellite Tracking and Backup Navigation System

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Issue Date
2013-01-25
Publisher
The Institute of Navigation (ION)
Citation
Proceedings of the 2012 International Technical Meeting of The Institute of Navigation, Newport Beach, CA, January 2012, pp. 812-819
Keywords
공학
Description
author's final manuscript
Abstract
In the recent years, it is very common using GNSS
receiver for the LEO satellite navigation and tracking.
The system cost of navigation equipment for satellite
becomes very low compare to other satellite navigation
and tracking system. The accuracy of GNSS receiver is
quite higher than other satellite navigation system. But
there must be a backup navigation system for situations
the GNSS receiver does not working or the GNSS system
does not service. When these situations happened satellite
cannot operate properly any more even worst case lost its
own position. Satellite rotates around the Earth in the
space, so we can predict satellite position and velocity for
some period. But the errors of numerical orbit
propagation method grow enormously with time. The
reason of growing error of numerical orbit propagation
method is due to that the space model we use is not fully
describes real space. Another reason of growing error of orbit prediction is due to the limited accuracy of satellite.
This is the main error source of orbit propagation; it is
quite difficult work to modeling the dynamics of satellite.
In this paper, we purposed combined numerical-empirical
orbit propagation method to improve this error. The orbit
prediction error was analyzed by empirical component
parts in the CW frame (Local Vertical Local Horizontal
frame). Residual error show very periodic characteristic
in CW frame. We use this character when numerical orbit
propagation. First, we generated orbit using numerical
orbit propagation method for future time which was
assumed GNSS receiver did not work. Residuals are
generated using numerical simulated orbit and true orbit
data. The residuals are analyzed in CW frame and
compressed into Fourier series coefficients. This
coefficient are used when predict the residuals for the
prediction time we assumed future. We did some
simulation to verify our purposed algorithm, and the
results show that using one day of orbit data we can
reduce the orbit prediction error under one meter.
Language
English
URI
https://hdl.handle.net/10371/81127
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Others_기계항공공학부
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