SGP4 Orbit Determination

作者：David Vallado, Paul Crawford · 发表于：AIAA/AAS Astrodynamics Specialist Conference and Exhibit · 年份：2008 · DOI：10.2514/6.2008-6770 · 被引用次数：250 · 研究领域：Astro and Planetary Science、Spacecraft Dynamics and Control、Space Satellite Systems and Control

In 2006, an updated version of SGP4 was presented for general use. The propagation routine relies on Two-Line Element (TLE) set data provided by the U.S. Government for several decades. Many independent organizations have access to observations, or ephemerides developed with other programs. Because the TLE is a compact means to obtain modestly accurate and fast calculations, it is desirable to have an orbit determination package that is compatible with the aforementioned code. This paper presents the code, test cases, and discussion of computer code to produce TLE data from an externally derived ephemeris. Initial code is also developed for processing raw observations. I. INTRODUCTION AND HISTORY he Simplified General Perturbations (SGP) model series began development in the 1960s (Lane 1965), and became operational in the early 1970s (Lane and Cranford, 1969). A variety of publications presented the mathematical theory, and the paper by Vallado et al. (2006) tracks the history of these publications. Unfortunately, there has never been a release of any kind of differential correction code to implement the SGP4