Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit

Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit

This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the s...

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Main Author: W. A. Rahoma
Format: Article
Language:English
Published: Korean Space Science Society (KSSS) 2014-09-01
Series:Journal of Astronomy and Space Sciences
Subjects:
Third-body perturbations
averaged model
long period perturbations
Online Access:http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2014/v31n3/OJOOBS_2014_v31n3_199.pdf
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spelling doaj-870b4e21d39b479396581afb7518a6c12020-11-24T22:34:22ZengKorean Space Science Society (KSSS)Journal of Astronomy and Space Sciences2093-55872093-14092014-09-0131319920410.5140/JASS.2014.31.3.199Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical OrbitW. A. Rahoma0Department of Astronomy, Faculty of Science, Cairo University, 12613, EgyptThis paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2014/v31n3/OJOOBS_2014_v31n3_199.pdfThird-body perturbationsaveraged modellong period perturbations
collection DOAJ
language English
format Article
sources DOAJ
author W. A. Rahoma
spellingShingle W. A. Rahoma
Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
Journal of Astronomy and Space Sciences
Third-body perturbations
averaged model
long period perturbations
author_facet W. A. Rahoma
author_sort W. A. Rahoma
title Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
title_short Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
title_full Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
title_fullStr Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
title_full_unstemmed Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
title_sort orbital elements evolution due to a perturbing body in an inclined elliptical orbit
publisher Korean Space Science Society (KSSS)
series Journal of Astronomy and Space Sciences
issn 2093-5587
2093-1409
publishDate 2014-09-01
description This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.
topic Third-body perturbations
averaged model
long period perturbations
url http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2014/v31n3/OJOOBS_2014_v31n3_199.pdf
work_keys_str_mv AT warahoma orbitalelementsevolutionduetoaperturbingbodyinaninclinedellipticalorbit
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