Abstract
In this study an integrated Newton-Raphson Method (NRM)/Extended Kalman Filter (EKF) Global Positioning System (GPS) based orbit determination for a Low Earth Orbit (LEO) satellite method is presented. The NRM and EKF algorithms are combined to estimate satellite's position and velocity vector components, respectively. Coarse position values computed at NRM preprocessing step are provided as measurement input to EKF algorithm. Orbital motion of LEO satellite is modelled with Keplerian and Newtonian equations taking into consideration the J2 perturbation effect caused by Earth's oblateness. Compared to traditional methods, utilizing such a preprocessing block (NRM) in filter design considerably reduces the complexity of the filter algorithm.
| Original language | English |
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| Title of host publication | 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings |
| Publisher | Institute of Electrical and Electronics Engineers Inc. |
| Pages | 462-467 |
| Number of pages | 6 |
| ISBN (Electronic) | 9781467382922 |
| DOIs | |
| Publication status | Published - 21 Sept 2016 |
| Event | 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Florence, Italy Duration: 21 Jun 2016 → 23 Jun 2016 |
Publication series
| Name | 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings |
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Conference
| Conference | 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 |
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| Country/Territory | Italy |
| City | Florence |
| Period | 21/06/16 → 23/06/16 |
Bibliographical note
Publisher Copyright:© 2016 IEEE.
Keywords
- Extended Kalman Filter (EKF)
- Global Positioning System (GPS)
- Newton-Raphson Method (NRM)
- Orbit Determination