Analysis of metric radar observations of a ballistic object above a rotating oblate spheroid.

摘要

This work focuses on the determination of motion parameters for artificial Earth satellites using observations (time, range, azimuth, and elevation) collected from a stationary ground based radar. The Earth Centered Inertial (ECI) State Vector (time, X, Y, Z, X˙, Y˙, Ż) will be derived and the accuracy examined as a function of processing technique, radar accuracy, and Earth gravitational model. The State Vector generation techniques investigated include: Kepler (three position measurements), Gauss (two position and time measurements), and data fitting techniques (N position and time measurements). The data fitting technique combines an iterated data filtering approach with linear, quadratic, and polynomial least squares data fitting techniques. The polynomial least squares fit is shown to provide the most consistent and accurate results.