Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit

The dynamics of relative motion in a perturbed orbital environment are exploited based on Gauss’ and Cowell’s variational equations. The inertial coordinate frame and relative coordinate frame (Hill frame) are used, and a linear high fidelity model is developed to describe the relative motion. This...

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Main Authors:	Okasha, Mohamed Elsayed Aly Abd Elaziz, Newman, Brett
Format:	Article
Language:	English English
Published:	The Korean Society for Aeronautical & Space Sciences 2015
Subjects:	TL500 Aeronautics TL787 Astronautics
Online Access:	http://irep.iium.edu.my/42772/ http://irep.iium.edu.my/42772/ http://irep.iium.edu.my/42772/ http://irep.iium.edu.my/42772/1/8%2877-88%2914-064.pdf http://irep.iium.edu.my/42772/4/42772-_wos%2Cscopus.pdf

id	iium-42772
recordtype	eprints
spelling	iium-427722017-08-18T02:02:37Z http://irep.iium.edu.my/42772/ Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit Okasha, Mohamed Elsayed Aly Abd Elaziz Newman, Brett TL500 Aeronautics TL787 Astronautics The dynamics of relative motion in a perturbed orbital environment are exploited based on Gauss’ and Cowell’s variational equations. The inertial coordinate frame and relative coordinate frame (Hill frame) are used, and a linear high fidelity model is developed to describe the relative motion. This model takes into account the primary gravitational and atmospheric drag perturbations. Then, this model is used in the design of a navigation, guidance, and control system of a chaser vehicle to approach towards and to depart from a target vehicle in proximity operations. Relative navigation uses an extended Kalman filter based on this relative model to estimate the relative position/velocity of the chaser vehicle with respect to the target vehicle. This filter uses the range and angle measurements of the target relative to the chaser from a simulated LIDAR system. The corresponding measurement models, process noise matrix, and other filter parameters are provided. Numerical simulations are performed to assess the precision of this model with respect to the full nonlinear model. The analyses include the navigation errors and trajectory dispersions. The Korean Society for Aeronautical & Space Sciences 2015-03 Article PeerReviewed application/pdf en http://irep.iium.edu.my/42772/1/8%2877-88%2914-064.pdf application/pdf en http://irep.iium.edu.my/42772/4/42772-_wos%2Cscopus.pdf Okasha, Mohamed Elsayed Aly Abd Elaziz and Newman, Brett (2015) Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit. International Journal of Aeronautical and Space Sciences, 16 (1). pp. 77-88. ISSN 2093-2480 (O), 2093-274X (P) E-ISSN 2093-2480 http://ijass.org/On_line/admin/files/8(77~88)14-064.pdf http://dx.doi.org/10.5139/IJASS.2015.16.1.77
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TL500 Aeronautics TL787 Astronautics
spellingShingle	TL500 Aeronautics TL787 Astronautics Okasha, Mohamed Elsayed Aly Abd Elaziz Newman, Brett Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit
description	The dynamics of relative motion in a perturbed orbital environment are exploited based on Gauss’ and Cowell’s variational equations. The inertial coordinate frame and relative coordinate frame (Hill frame) are used, and a linear high fidelity model is developed to describe the relative motion. This model takes into account the primary gravitational and atmospheric drag perturbations. Then, this model is used in the design of a navigation, guidance, and control system of a chaser vehicle to approach towards and to depart from a target vehicle in proximity operations. Relative navigation uses an extended Kalman filter based on this relative model to estimate the relative position/velocity of the chaser vehicle with respect to the target vehicle. This filter uses the range and angle measurements of the target relative to the chaser from a simulated LIDAR system. The corresponding measurement models, process noise matrix, and other filter parameters are provided. Numerical simulations are performed to assess the precision of this model with respect to the full nonlinear model. The analyses include the navigation errors and trajectory dispersions.
format	Article
author	Okasha, Mohamed Elsayed Aly Abd Elaziz Newman, Brett
author_facet	Okasha, Mohamed Elsayed Aly Abd Elaziz Newman, Brett
author_sort	Okasha, Mohamed Elsayed Aly Abd Elaziz
title	Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit
title_short	Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit
title_full	Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit
title_fullStr	Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit
title_full_unstemmed	Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit
title_sort	modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit
publisher	The Korean Society for Aeronautical & Space Sciences
publishDate	2015
url	http://irep.iium.edu.my/42772/ http://irep.iium.edu.my/42772/ http://irep.iium.edu.my/42772/ http://irep.iium.edu.my/42772/1/8%2877-88%2914-064.pdf http://irep.iium.edu.my/42772/4/42772-_wos%2Cscopus.pdf
first_indexed	2023-09-18T21:00:57Z
last_indexed	2023-09-18T21:00:57Z
_version_	1777410619637497856

Modeling, dynamics and control of spacecraft relative motion in a perturbed keplerian orbit

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