Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation

In this study, an algorithm to identify the maneuvers of a satellite is developed by comparing the Keplerian elements acquired from the two-line elements (TLEs) and Keplerian elements propagated from simplified perturbation models. TLEs contain a specific set of orbital elements, whereas the simplif...

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Autores principales:	Arvind Mukundan, Hsiang-Chen Wang
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	two-line elements simplified perturbation models Keplarian elements trial & error and maneuver detection Technology T Engineering (General). Civil engineering (General) TA1-2040 Biology (General) QH301-705.5 Physics QC1-999 Chemistry QD1-999
Acceso en línea:	https://doaj.org/article/10245884c71c48ab9b1f374fff0425cf
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spelling	oai:doaj.org-article:10245884c71c48ab9b1f374fff0425cf2021-11-11T15:14:37ZSimplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation10.3390/app1121101812076-3417https://doaj.org/article/10245884c71c48ab9b1f374fff0425cf2021-10-01T00:00:00Zhttps://www.mdpi.com/2076-3417/11/21/10181https://doaj.org/toc/2076-3417In this study, an algorithm to identify the maneuvers of a satellite is developed by comparing the Keplerian elements acquired from the two-line elements (TLEs) and Keplerian elements propagated from simplified perturbation models. TLEs contain a specific set of orbital elements, whereas the simplified perturbation models are used to propagate the state vectors at a given time. By comparing the corresponding Keplerian elements derived from both methods, a satellite’s maneuver is identified. This article provides an outline of the working methodology and efficacy of the method. The function of this approach is evaluated in two case studies, i.e., TOPEX/Poseidon and Envisat, whose maneuver histories are available. The same method is implemented to identify the station-keeping maneuvers for TDRS-3, whose maneuver history is not available. Results derived from the analysis indicate that maneuvers with a magnitude of even as low as cm/s are detected when the detection parameters are calibrated properly.Arvind MukundanHsiang-Chen WangMDPI AGarticletwo-line elementssimplified perturbation modelsKeplarian elementstrial & error and maneuver detectionTechnologyTEngineering (General). Civil engineering (General)TA1-2040Biology (General)QH301-705.5PhysicsQC1-999ChemistryQD1-999ENApplied Sciences, Vol 11, Iss 10181, p 10181 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	two-line elements simplified perturbation models Keplarian elements trial & error and maneuver detection Technology T Engineering (General). Civil engineering (General) TA1-2040 Biology (General) QH301-705.5 Physics QC1-999 Chemistry QD1-999
spellingShingle	two-line elements simplified perturbation models Keplarian elements trial & error and maneuver detection Technology T Engineering (General). Civil engineering (General) TA1-2040 Biology (General) QH301-705.5 Physics QC1-999 Chemistry QD1-999 Arvind Mukundan Hsiang-Chen Wang Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation
description	In this study, an algorithm to identify the maneuvers of a satellite is developed by comparing the Keplerian elements acquired from the two-line elements (TLEs) and Keplerian elements propagated from simplified perturbation models. TLEs contain a specific set of orbital elements, whereas the simplified perturbation models are used to propagate the state vectors at a given time. By comparing the corresponding Keplerian elements derived from both methods, a satellite’s maneuver is identified. This article provides an outline of the working methodology and efficacy of the method. The function of this approach is evaluated in two case studies, i.e., TOPEX/Poseidon and Envisat, whose maneuver histories are available. The same method is implemented to identify the station-keeping maneuvers for TDRS-3, whose maneuver history is not available. Results derived from the analysis indicate that maneuvers with a magnitude of even as low as cm/s are detected when the detection parameters are calibrated properly.
format	article
author	Arvind Mukundan Hsiang-Chen Wang
author_facet	Arvind Mukundan Hsiang-Chen Wang
author_sort	Arvind Mukundan
title	Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation
title_short	Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation
title_full	Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation
title_fullStr	Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation
title_full_unstemmed	Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation
title_sort	simplified approach to detect satellite maneuvers using tle data and simplified perturbation model utilizing orbital element variation
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/10245884c71c48ab9b1f374fff0425cf
work_keys_str_mv	AT arvindmukundan simplifiedapproachtodetectsatellitemaneuversusingtledataandsimplifiedperturbationmodelutilizingorbitalelementvariation AT hsiangchenwang simplifiedapproachtodetectsatellitemaneuversusingtledataandsimplifiedperturbationmodelutilizingorbitalelementvariation
_version_	1718436057502973952

Simplified Approach to Detect Satellite Maneuvers Using TLE Data and Simplified Perturbation Model Utilizing Orbital Element Variation

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