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

Weiping Li, Hongxing Qiu, Dang Jin Qi

Open publisher page 2 citations

Abstract

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 of the 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 converted from OKE and which is based on SGP4/SDP4 model.The simulation test and actual use show that the method is effective and the result TLE therewith meets the demand on orbit prediction precision.

About this research paper

What this paper is about

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 of the 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 converted from OKE and which is based on SGP4/SDP4 model.The simulation test and actual use show that the method is effective and the result TLE therewith meets the demand on orbit prediction precision.

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Available abstract

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 of the 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 converted from OKE and which is based on SGP4/SDP4 model.The simulation test and actual use show that the method is effective and the result TLE therewith meets the demand on orbit prediction precision.

Key concepts: Osculating circle, Frozen orbit, Orbital elements, Orbit (dynamics), Orbit determination, Perturbation (astronomy), Orbital mechanics, Spacecraft

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