Estimating Keplerian Elements for New Satellite Launches

摘要

Satellite tracking software requires a mathematical orbit description to predict a satellite'slocation and motion. An important pre-launch activity for new satellites is estimatingKeplerian elements for tracking the satellite in the early stages, before more refined orbitaldata is available. The estimation process uses available information including the launchsite location, launch date and time, and planned orbit (apogee and perigee altitudes andinclination angle). Since launch date and time may change one or more times, themethod presented develops the orbit as a time-independent position and velocity statevector that can be readily used produce the corresponding Keplerian elements once thelaunch date and time is known. The methods for producing the time-independent statevector as well as for computing the Keplerian elements are provided. Both stages of theprocess are encapsulated in software tools available for download from the Internet.