Abstract
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.
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Published version (
Free)
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
