Low inclination circular orbits for remote sensing satellites

This paper investigates the design methodology of low Earth inclined circular orbits for remote sensing satellites to satisfy certain mission requirements and constrains such as coverage, resolution, illumination conditions and attitude maneuvers capabilities. Although sun synchronous orbit (SSO)...

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Main Authors:	Kamalaldin, Karim, Okasha, Mohamed Elsayed Aly Abd Elaziz
Format:	Article
Language:	English English
Published:	Trans Tech Publications Ltd., Switzerland 2014
Subjects:	TA168 Systems engineering TA174 Engineering design
Online Access:	http://irep.iium.edu.my/38402/ http://irep.iium.edu.my/38402/ http://irep.iium.edu.my/38402/ http://irep.iium.edu.my/38402/1/AMM.629.298.pdf http://irep.iium.edu.my/38402/4/38402_Low%20inclination%20circular%20orbits%20for%20remote%20sensing%20satellites__SCOPUS.pdf

id	iium-38402
recordtype	eprints
spelling	iium-384022017-09-19T04:23:50Z http://irep.iium.edu.my/38402/ Low inclination circular orbits for remote sensing satellites Kamalaldin, Karim Okasha, Mohamed Elsayed Aly Abd Elaziz TA168 Systems engineering TA174 Engineering design This paper investigates the design methodology of low Earth inclined circular orbits for remote sensing satellites to satisfy certain mission requirements and constrains such as coverage, resolution, illumination conditions and attitude maneuvers capabilities. Although sun synchronous orbit (SSO) proved to be a good candidate for most remote sensing applications due to its constant lighting conditions and global coverage, low inclined orbits are distinguished by long ground track especially if the target area of concern has horizontal rectangular border. With that respect, low inclined orbits may lead to improvement of the satellite imaging accessibility to the target area per day or reduction of satellite revisit time compared to SSO. This paper exploits these characteristics for low inclined orbits. The target area considered in simulation is between 220 and 320 N latitude lines with 2.5 m ground sample resolution. The satellite maximum rolling capability is 350 and the sun elevation angle is constrained between 300 and 700 for purpose of maximizing the quality of the obtained images. Matlab and STK software are employed to define the initial orbital parameters to meet these conditions for a low inclined orbit. Trans Tech Publications Ltd., Switzerland 2014 Article PeerReviewed application/pdf en http://irep.iium.edu.my/38402/1/AMM.629.298.pdf application/pdf en http://irep.iium.edu.my/38402/4/38402_Low%20inclination%20circular%20orbits%20for%20remote%20sensing%20satellites__SCOPUS.pdf Kamalaldin, Karim and Okasha, Mohamed Elsayed Aly Abd Elaziz (2014) Low inclination circular orbits for remote sensing satellites. Applied Mechanics and Materials, 629. pp. 298-303. ISSN 1660-9336 http://www.scientific.net/AMM/details 10.4028/www.scientific.net/AMM.629.298
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TA168 Systems engineering TA174 Engineering design
spellingShingle	TA168 Systems engineering TA174 Engineering design Kamalaldin, Karim Okasha, Mohamed Elsayed Aly Abd Elaziz Low inclination circular orbits for remote sensing satellites
description	This paper investigates the design methodology of low Earth inclined circular orbits for remote sensing satellites to satisfy certain mission requirements and constrains such as coverage, resolution, illumination conditions and attitude maneuvers capabilities. Although sun synchronous orbit (SSO) proved to be a good candidate for most remote sensing applications due to its constant lighting conditions and global coverage, low inclined orbits are distinguished by long ground track especially if the target area of concern has horizontal rectangular border. With that respect, low inclined orbits may lead to improvement of the satellite imaging accessibility to the target area per day or reduction of satellite revisit time compared to SSO. This paper exploits these characteristics for low inclined orbits. The target area considered in simulation is between 220 and 320 N latitude lines with 2.5 m ground sample resolution. The satellite maximum rolling capability is 350 and the sun elevation angle is constrained between 300 and 700 for purpose of maximizing the quality of the obtained images. Matlab and STK software are employed to define the initial orbital parameters to meet these conditions for a low inclined orbit.
format	Article
author	Kamalaldin, Karim Okasha, Mohamed Elsayed Aly Abd Elaziz
author_facet	Kamalaldin, Karim Okasha, Mohamed Elsayed Aly Abd Elaziz
author_sort	Kamalaldin, Karim
title	Low inclination circular orbits for remote sensing satellites
title_short	Low inclination circular orbits for remote sensing satellites
title_full	Low inclination circular orbits for remote sensing satellites
title_fullStr	Low inclination circular orbits for remote sensing satellites
title_full_unstemmed	Low inclination circular orbits for remote sensing satellites
title_sort	low inclination circular orbits for remote sensing satellites
publisher	Trans Tech Publications Ltd., Switzerland
publishDate	2014
url	http://irep.iium.edu.my/38402/ http://irep.iium.edu.my/38402/ http://irep.iium.edu.my/38402/ http://irep.iium.edu.my/38402/1/AMM.629.298.pdf http://irep.iium.edu.my/38402/4/38402_Low%20inclination%20circular%20orbits%20for%20remote%20sensing%20satellites__SCOPUS.pdf
first_indexed	2023-09-18T20:55:10Z
last_indexed	2023-09-18T20:55:10Z
_version_	1777410255843491840

Low inclination circular orbits for remote sensing satellites

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