In this paper, we have proposed orbit determination algorithm using DGPS for Low Earth Orbit (LEO) satellite as alternative about conventional methods and developed DOPS environment for simulation. The conventional radar tracking or optical method has some problems (more station needed for low orbit satellite, high cost, low accuracy and dependence of operation). But our DGPS orbit determination method can solve these problems. We have considered almost effective perturbations (asymmetry gravitational force, Sun's gravity, Moon's gravity, Solar pressure, Air drag) on ECI coordinate and showed their effects graphically. Using Extended Kalman Filter we have made linear system model and estimated state variables. To test DOPS orbit determination virtually u sing this algorithm, we have simulated DGPS environment in space including most effects (GPS satellites arrangement, clock errors, ionosphere delay, etc.). From this, we could confirm good performance and possibility of our proposed algorithm.
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