Iterative method has a wide range of applications in various fields. A classical osculating orbit element set and a two line element sets (TLE) are often used to describe the orbit of spacecraft, but the conversion from a classical osculating orbit element set to a TLE is seldom described. A numerical iterative method is described in this paper, by which a classical osculating orbit element set can be converted to a TLE. Experiments show that the method is effective and resulted TLEs can meet the required.
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