doi:10.1088/1742-6596/1530/1/012127

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Publication Date

Fri May 01 2020

Journal Name

Journal Of Physics: Conference Series

Volume

1530

DOI

10.1088/1742-6596/1530/1/012127

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Determination the optimum orbit for low Earth satellites by changing the eccentricity

Raha

Abdul-Rahman

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Abstract<p>The main objective of this paper is to determine an acceptable value of eccentricity for the satellites in a Low Earth Orbit LEO that are affected by drag perturbation only. The method of converting the orbital elements into state vectors was presented. Perturbed equation of motion was numerically integrated using 4<sup>th</sup> order Runge-Kutta’s method and the perturbation in orbital elements for different altitudes and eccentricities were tested and analysed during 84.23 days. The results indicated to the value of semi major axis and eccentricity at altitude 200 km and eccentricity 0.001are more stable. As well, at altitude 600 km and eccentricity 0.01, but at 800 km and eccentricities (0.01, 0.05 and 0.1) the stability of the orbit was not depending strongly on eccentricity value, because the effect of the drag is too small.</p>