Study On Satellite On-board Orbit Prediction Algorithm And Orbital Maneuver Simulation

Enhancing on-board navigation ability, alleviating ground system's burden and cutting down the cost of space mission, spacecraft autonomous navigation system is significantly important. Autonomous navigation will simplify ground system on spacecraft tracking and routine orbit determination. The development of on-board computer and the increasing requirement for orbit prediction precision, promote the update of on-board orbit prediction algorithm. In addition, extensive attention has been already paid to developing the stable orbital control system by the domestic and foreign researchers, which is a key technology of high precise small satellite. In this thesis, spacecraft on-board orbit prediction algorithm and orbital maneuver simulation are discussed respectively. The main work is followed: Establishing the force models for LEO (Low Earth Orbit) spacecraft, considering the various perturbations including the Earth gravity, the lunisolar forces, solar radiation and atmospheric drag. Working on the spacecraft simulation system and its user interface, mainly on orbit dynamics model and its implementation. Giving a new satellite ephemeris computation method. It is difficult for the traditional methods to satisfy the increasing precise requirement in future. With the great improvement of on-board system capability, it is feasible to predict more precise satellite orbit on-board. A numerical algorithm for on-board orbit prediction is presented for the LEO spacecraft, by applying the simplified dynamics method and RK4 integrator embedded with the interpolation method. Earth observation satellites mostly operate on nearly circular sun synchronization orbits. Their orbital maneuvers are usually accomplished among circular different...