Numerical estimates of the perturbations of the orbit elements of a winged earth satellite due to the satellite shape

The perturbations of the orbit elements of a cylindrical satellite with symmetric wings (solar panels) during translational-rotational motion around a spherical earth are estimated numerically using a specific example. It is shown that the shape of the winged cylindrical satellite considered here has practically no effect on the Delaunay orbit elements. The mean motion of the satellite, however, changes significantly with time.