Covariance propagation of two-line element data

In the space debris collision warning based on the collision probability, the collision probability is calculated by collision time and speed displacement vectors of two targets and the calculated error covariance information. In General, using the SGP4 model could get the satellite's ephemeris...

Full description

Saved in:
Bibliographic Details
Published in2016 Chinese Control and Decision Conference (CCDC) pp. 3836 - 3841
Main Authors Yurong, Huo, Zhi, Li, Lei, Han
Format Conference Proceeding Journal Article
LanguageEnglish
Published IEEE 01.05.2016
Subjects
Collision dynamics
collision warning
Covariance
Covariance matrices
covariance propagation
Electronics
Errors
Fitting
Fittings
Mathematical model
Mathematical models
orbit error
Orbital elements
Orbitals
Orbits
Satellites
Space vehicles
Online AccessGet full text

Cover

More Information
Summary:In the space debris collision warning based on the collision probability, the collision probability is calculated by collision time and speed displacement vectors of two targets and the calculated error covariance information. In General, using the SGP4 model could get the satellite's ephemeris, but unfortunately, the SGP4 orbital data, in the form of two-line element sets (TLE) containing mean orbital elements of satellite does not include the accuracy of orbit, so we need to use specified method to calculate the orbit error covariance. This paper uses historical TLE data to calculate the covariance matrix of orbital error and analyze the covariance propagation by function fitting. Finally, comparing the results of the covariance propagation with the covariance calculated by HPOP model.
Bibliography:ObjectType-Article-2
SourceType-Scholarly Journals-1
ObjectType-Conference-1
ObjectType-Feature-3
content type line 23
SourceType-Conference Papers & Proceedings-2
ISSN:1948-9447
DOI:10.1109/CCDC.2016.7531654