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The Taylor series is defined by the f and g series. The solution to the satellite's equation of motion is
expanding to generate Taylor series through the coefficients f and g. In this study, the orbit equation in a perifocal system
is solved using the Taylor series, which is based on time changing. A program in matlab is designed to apply the results
for a geocentric satellite in low orbit (height from perigee, hp= 622 km). The input parameters were the initial distance
from perigee, the initial time, eccentricity, true anomaly, position, and finally the velocity. The output parameters were
the final distance from perigee and the final time values. The results of radial distance as opposed to time were plotted for
dissimilar times in
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