International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Earth Albedo perturbations on Low Earth Orbit Cubesats

  • Khalifa, N.S. (Mathematics Department, Deanship of Preparatory Year- Girls Branch, University of Hail (UOH), Space Research Lab, National Research Institute of Astronomy and Geophysics (NRIAG)) ;
  • Sharaf-Eldin, T.E. (Mathematics Department, Deanship of Preparatory Year- Girls Branch, University of Hail (UOH), Electrical. Eng. Dept., Faculty of Engineering, Alexandria University)
  • Received : 2013.04.22
  • Accepted : 2013.06.12
  • Published : 2013.06.30
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Abstract

This work investigates the orbital perturbations of the cubesats that lie on LEO due to Earth albedo. The motivation for this paper originated in the investigation of the orbital perturbations for closed- Earth pico-satellites due to the sunlight reflected by the Earth (the albedo). Having assumed that the Sun lies on the equator, the albedo irradiance is calculated using a numerical model in which irradiance depends on the geographical latitude, longitude and altitude of the satellite. However, in the present work the longitude dependency is disregarded. Albedo force and acceleration components are formulated using a detailed model in a geocentric equatorial system in which the Earth is an oblate spheroid. Lagrange planetary equations in its Gaussian form are used to analyze the orbital changes when $e{\neq}0$ and $i{\neq}0$. Based on the Earth's reflectivity data measured by NASA Total Ozone Mapping Spectrometer (TOMS project), the orbital perturbations are calculated for some cubesats. The outcome of the numerical test shows that the albedo force has a significant contribution on the orbital perturbations of the pico-satellite which can affect the satellite life time.

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