Solar pressure induced perturbations of orbital elements for the Communications Technology Satellite

The orbital perturbations induced by the solar radiation pressure is studied for the Communications Technology Satellite. The problem is formulated for the satellite in an arbitrary orbit accounting for both planar and perpendicular forces together with the time dependent character of the solar aspect angle. The singularities arising from small eccentricity are eliminated by suitable transformations. The resulting equations are integrated numerically using a Runge-Kutta procedure with built-in error control. A secular East-West deviation of the satellite from the desired overhead position is observed. The feasibility of utilizing permissible solar panel rotations to eliminate the secular drift is established.