Simple orbit determination using GPS based on a least-squares algorithm employing sequential Givens rotations (Q954561)

Summary: We propose a low-cost computer procedure to determine the orbit of an artificial satellite by using short arc data from an onboard GPS receiver. Pseudoranges are used as measurements to estimate the orbit via recursive least squares method. The algorithm applies orthogonal Givens rotations for solving recursive and sequential orbit determination problems. To assess the procedure, it was applied to the TOPEX/POSEIDON satellite for data batches of one orbital period (approximately two hours), and force modelling, due to the full JGM-2 gravity field model, was considered. When compared with the reference Precision Orbit Ephemeris (POE) of JPL/NASA, the results have indicated that precision better than 9\thinspace m is easily obtained, even when short batches of data are used.