Determining optimal orbital path of a nanosatellite for efficient exploitation of the solar energy captured

Small satellites for earth observation are an important ongoing development in space research. Small satellites are usually powered from a solar energy system. In order to maximize the solar energy captured on small satellites, orbit path selection becomes an important parameter. In this work, we have conducted some numerical studies for future small satellites (nanosatellites) developed within the PERSEUS project. We have determined the optimal variation of the orbit angle (the minimum angle between the satellite's orbit plane and solar vector), in order to obtain an eclipse duration as short as possible, and to maintain the angle value as long as possible thus maximizing the solar energy captured by its photovoltaic panels.