Integrated NRM/EKF for LEO satellite GPS based orbit determination

Murat Bagci; Chingiz Hajiyev

doi:10.1109/MetroAeroSpace.2016.7573259

Integrated NRM/EKF for LEO satellite GPS based orbit determination

Murat Bagci
, Chingiz Hajiyev

Uçak Mühendisliği Bölümü

Turkish Air Force Academy

Araştırma sonucu: Kitap/Rapor/Konferans Bildirisinde Bölüm › Konferans katkısı › bilirkişi

6 Atıf (Scopus)

Özet

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.

Orijinal dil	İngilizce
Ana bilgisayar yayını başlığı	3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings
Yayınlayan	Institute of Electrical and Electronics Engineers Inc.
Sayfalar	462-467
Sayfa sayısı	6
ISBN (Elektronik)	9781467382922
DOI'lar	https://doi.org/10.1109/MetroAeroSpace.2016.7573259
Yayın durumu	Yayınlandı - 21 Eyl 2016
Etkinlik	3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Florence, Italy Süre: 21 Haz 2016 → 23 Haz 2016

Yayın serisi

Adı	3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings

???event.eventtypes.event.conference???

???event.eventtypes.event.conference???	3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016
Ülke/Bölge	Italy
Şehir	Florence
Periyot	21/06/16 → 23/06/16

Bibliyografik not

Publisher Copyright:
© 2016 IEEE.

Belgeye Erişim

10.1109/MetroAeroSpace.2016.7573259

Diğer Dosyalar ve Linkler

Link to publication in Scopus

Alıntı Yap

Bagci, M., & Hajiyev, C. (2016). Integrated NRM/EKF for LEO satellite GPS based orbit determination. In 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings (pp. 462-467). Makale 7573259 (3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/MetroAeroSpace.2016.7573259

@inproceedings{899413bad2df4dd599a203596c8b6e79,

title = "Integrated NRM/EKF for LEO satellite GPS based orbit determination",

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.",

keywords = "Extended Kalman Filter (EKF), Global Positioning System (GPS), Newton-Raphson Method (NRM), Orbit Determination",

author = "Murat Bagci and Chingiz Hajiyev",

note = "Publisher Copyright: {\textcopyright} 2016 IEEE.; 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 ; Conference date: 21-06-2016 Through 23-06-2016",

year = "2016",

month = sep,

day = "21",

doi = "10.1109/MetroAeroSpace.2016.7573259",

language = "English",

series = "3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings",

publisher = "Institute of Electrical and Electronics Engineers Inc.",

pages = "462--467",

booktitle = "3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings",

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}

Bagci, M & Hajiyev, C 2016, Integrated NRM/EKF for LEO satellite GPS based orbit determination. in 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings., 7573259, 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings, Institute of Electrical and Electronics Engineers Inc., pp. 462-467, 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016, Florence, Italy, 21/06/16. https://doi.org/10.1109/MetroAeroSpace.2016.7573259

Integrated NRM/EKF for LEO satellite GPS based orbit determination. / Bagci, Murat; Hajiyev, Chingiz.
3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings. Institute of Electrical and Electronics Engineers Inc., 2016. p. 462-467 7573259 (3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings).

Araştırma sonucu: Kitap/Rapor/Konferans Bildirisinde Bölüm › Konferans katkısı › bilirkişi

TY - GEN

T1 - Integrated NRM/EKF for LEO satellite GPS based orbit determination

AU - Bagci, Murat

AU - Hajiyev, Chingiz

PY - 2016/9/21

Y1 - 2016/9/21

N2 - 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.

AB - 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.

KW - Extended Kalman Filter (EKF)

KW - Global Positioning System (GPS)

KW - Newton-Raphson Method (NRM)

KW - Orbit Determination

UR - https://www.scopus.com/pages/publications/84991778547

U2 - 10.1109/MetroAeroSpace.2016.7573259

DO - 10.1109/MetroAeroSpace.2016.7573259

M3 - Conference contribution

AN - SCOPUS:84991778547

T3 - 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings

SP - 462

EP - 467

BT - 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings

PB - Institute of Electrical and Electronics Engineers Inc.

T2 - 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016

Y2 - 21 June 2016 through 23 June 2016

ER -

Bagci M, Hajiyev C. Integrated NRM/EKF for LEO satellite GPS based orbit determination. In 3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings. Institute of Electrical and Electronics Engineers Inc. 2016. p. 462-467. 7573259. (3rd IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2016 - Proceedings). doi: 10.1109/MetroAeroSpace.2016.7573259

Integrated NRM/EKF for LEO satellite GPS based orbit determination

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