A Study on Conversion from Osculating Orbit Element to Two Line Element

Two-line element (TLE) is the special form of satellite orbit element, which is derived on the basis of the classical general perturbation theory and can be used together with NORAD's SGP4/ SDP4 orbital model to determine the position and velocity ofthe associated satellite. Osculating Kepler Element (OKE) and TLE are often used to describe the orbit of spacecraft, but few conversion methods from OKE to TLE are introduced. An iterative method is described in this paper, in which TLE can be convertedfrom OKE and which is based on SGP4/ SDP4 model. The simulation test and actual use show that the method is effective and theresult TLE therewith meets the demand on orbit prediction precision.