Abstract
The aim of this paper is to present the basic mathematical and theoretical knowledge of the
orbit geometry system of the satellite. Information about the orbit of the satellite system is
considered as the critical and main parts of the satellite design. The presented design model of the
orbit geometry is valid for mini satellites (100-500 kg), which are used for imaging missions. The
objective of the design model is to minimize the size, the mass, and the complexity of the satellite
so that it fits the envelope of the launching vehicle. The propulsion system and others equipments
of the satellite as the payload or the imaging system, on board computer system, data link and the
solar cells determine the size and mass of the satellite. An example of orbit geometry for a
satellite was described included the results of the design model.