Satellite Formation Flight Via NRM and EKF State Estimation Method

Tuncay Yunus Erkec; Chingiz Hajiyev

doi:10.1007/978-3-031-38446-2_32

Satellite Formation Flight Via NRM and EKF State Estimation Method

Tuncay Yunus Erkec^*, Chingiz Hajiyev

^*Corresponding author for this work

Department of Aeronautical Engineering

Turkish National Defence University

Research output: Chapter in Book/Report/Conference proceeding › Chapter › peer-review

Abstract

This chapter is devoted to the analysis of relative satellite vector estimations with extended Kalman filter (EKF) using the target and follower satellite positioning approach obtained by the Newton-Raphson method (NRM). In this study, target and follower satellite baseline values were determined as derived simulation data. Position states due to Earth-centered inertial (ECI) reference frame were obtained by Keplerian orbital parameters and Global Positioning System (GPS) receiver. The Pseudo-ranging model was used to determining the position of target and follower satellites. To simulate GPS receiver, random measurement errors were added to the actual distance between the target and follower satellites. With this study, satellite relative state vectors are obtained within the analysis scenario.

Original language	English
Title of host publication	Sustainable Aviation
Publisher	Springer Nature
Pages	281-287
Number of pages	7
DOIs	https://doi.org/10.1007/978-3-031-38446-2_32
Publication status	Published - 2024

Publication series

Name	Sustainable Aviation
Volume	Part F4680
ISSN (Print)	2730-7778
ISSN (Electronic)	2730-7786

Bibliographical note

Publisher Copyright:
© The Author(s), under exclusive license to Springer Nature Switzerland AG 2024.

Keywords

Cluster satellites
Extended Kalman filter
GPS
Newton-Raphson method
Pseudo-ranging model
Relative navigation
Satellite

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10.1007/978-3-031-38446-2_32

Cite this

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title = "Satellite Formation Flight Via NRM and EKF State Estimation Method",

abstract = "This chapter is devoted to the analysis of relative satellite vector estimations with extended Kalman filter (EKF) using the target and follower satellite positioning approach obtained by the Newton-Raphson method (NRM). In this study, target and follower satellite baseline values were determined as derived simulation data. Position states due to Earth-centered inertial (ECI) reference frame were obtained by Keplerian orbital parameters and Global Positioning System (GPS) receiver. The Pseudo-ranging model was used to determining the position of target and follower satellites. To simulate GPS receiver, random measurement errors were added to the actual distance between the target and follower satellites. With this study, satellite relative state vectors are obtained within the analysis scenario.",

keywords = "Cluster satellites, Extended Kalman filter, GPS, Newton-Raphson method, Pseudo-ranging model, Relative navigation, Satellite",

author = "Erkec, {Tuncay Yunus} and Chingiz Hajiyev",

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year = "2024",

doi = "10.1007/978-3-031-38446-2_32",

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T1 - Satellite Formation Flight Via NRM and EKF State Estimation Method

AU - Erkec, Tuncay Yunus

AU - Hajiyev, Chingiz

N1 - Publisher Copyright: © The Author(s), under exclusive license to Springer Nature Switzerland AG 2024.

PY - 2024

Y1 - 2024

N2 - This chapter is devoted to the analysis of relative satellite vector estimations with extended Kalman filter (EKF) using the target and follower satellite positioning approach obtained by the Newton-Raphson method (NRM). In this study, target and follower satellite baseline values were determined as derived simulation data. Position states due to Earth-centered inertial (ECI) reference frame were obtained by Keplerian orbital parameters and Global Positioning System (GPS) receiver. The Pseudo-ranging model was used to determining the position of target and follower satellites. To simulate GPS receiver, random measurement errors were added to the actual distance between the target and follower satellites. With this study, satellite relative state vectors are obtained within the analysis scenario.

AB - This chapter is devoted to the analysis of relative satellite vector estimations with extended Kalman filter (EKF) using the target and follower satellite positioning approach obtained by the Newton-Raphson method (NRM). In this study, target and follower satellite baseline values were determined as derived simulation data. Position states due to Earth-centered inertial (ECI) reference frame were obtained by Keplerian orbital parameters and Global Positioning System (GPS) receiver. The Pseudo-ranging model was used to determining the position of target and follower satellites. To simulate GPS receiver, random measurement errors were added to the actual distance between the target and follower satellites. With this study, satellite relative state vectors are obtained within the analysis scenario.

KW - Cluster satellites

KW - Extended Kalman filter

KW - GPS

KW - Newton-Raphson method

KW - Pseudo-ranging model

KW - Relative navigation

KW - Satellite

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M3 - Chapter

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SP - 281

EP - 287

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PB - Springer Nature

ER -

Satellite Formation Flight Via NRM and EKF State Estimation Method

Abstract

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