New Solar Radiation Pressure Force Model for Navigation

This paper presents a new force model for solar radiation pressure acting on a satellite. The model is based on a Fourier series representation of the satellite properties and the position of the sun with respect to the body. The perturbative effects on the satellite's orbit due to the solar radiation pressure are derived in full and subsequently averaged to determine the secular change in the orbit due to solar radiation pressure, as well as the short-period dynamics. The theory presented includes a methodology for analyzing the changes to the secular and short-period dynamics due to the spacecraft passing through the Earth's shadow. This preliminary study shows that for a spacecraft in a circular orbit with synchronous rotation, the secular effects of solar radiation can be described with only seven Fourier coefficients. The benefits of using this theory for navigation applications are discussed. Finally, an example based on the Gravity Recovery and Climate Experiment satellite illustrates the applicability of the theory presented.