Relative motion guidance, navigation and control for autonomous orbital rendezvous

In this paper, the dynamics of the relative motion problem in a perturbed orbital environment are exploited based on Gauss’ variational equations. The relative coordinate frame (Hill frame) is studied to describe the relative motion. A linear high fidelity model is developed to describe the relative...

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Main Authors:	Okasha, Mohamed Elsayed Aly Abd Elaziz, Newman, Brett
Format:	Article
Language:	English English
Published:	Instituto de Aeronautica e Espaco-IAE - Brazil 2014
Subjects:	TA168 Systems engineering TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering
Online Access:	http://irep.iium.edu.my/38405/ http://irep.iium.edu.my/38405/ http://irep.iium.edu.my/38405/ http://irep.iium.edu.my/38405/1/38405_Relative%20motion%20guidance%2C%20navigation.pdf http://irep.iium.edu.my/38405/2/38405_Relative%20motion%20guidance%2C%20navigation_SCOPUS.pdf

id	iium-38405
recordtype	eprints
spelling	iium-384052017-09-26T07:58:33Z http://irep.iium.edu.my/38405/ Relative motion guidance, navigation and control for autonomous orbital rendezvous Okasha, Mohamed Elsayed Aly Abd Elaziz Newman, Brett TA168 Systems engineering TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering In this paper, the dynamics of the relative motion problem in a perturbed orbital environment are exploited based on Gauss’ variational equations. The relative coordinate frame (Hill frame) is studied to describe the relative motion. A linear high fidelity model is developed to describe the relative motion. This model takes into account primary gravitational and atmospheric drag perturbations. In addition, this model is used in the design of a control, guidance, and navigation 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 and velocity of the chaser vehicle with respect to the target vehicle and the chaser attitude and gyros biases. This filter uses the range and angle measurements of the target relative to the chaser from a simulated Light Detection and Ranging (LIDAR) system, along with the star tracker and gyro measurements of the chaser. 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 navigations errors, trajectory dispersions, and attitude dispersions. Instituto de Aeronautica e Espaco-IAE - Brazil 2014-07 Article PeerReviewed application/pdf en http://irep.iium.edu.my/38405/1/38405_Relative%20motion%20guidance%2C%20navigation.pdf application/pdf en http://irep.iium.edu.my/38405/2/38405_Relative%20motion%20guidance%2C%20navigation_SCOPUS.pdf Okasha, Mohamed Elsayed Aly Abd Elaziz and Newman, Brett (2014) Relative motion guidance, navigation and control for autonomous orbital rendezvous. Journal of Aerospace Technology and Management, 6 (3). pp. 301-318. ISSN 1984-9648 E-ISSN 2175-9146 http://www.jatm.com.br/ojs/index.php/jatm/article/view/330 10.5028/jatm.v6i3.330
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 TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering
spellingShingle	TA168 Systems engineering TA329 Engineering mathematics. Engineering analysis TA349 Mechanics of engineering. Applied mechanics TJ212 Control engineering Okasha, Mohamed Elsayed Aly Abd Elaziz Newman, Brett Relative motion guidance, navigation and control for autonomous orbital rendezvous
description	In this paper, the dynamics of the relative motion problem in a perturbed orbital environment are exploited based on Gauss’ variational equations. The relative coordinate frame (Hill frame) is studied to describe the relative motion. A linear high fidelity model is developed to describe the relative motion. This model takes into account primary gravitational and atmospheric drag perturbations. In addition, this model is used in the design of a control, guidance, and navigation 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 and velocity of the chaser vehicle with respect to the target vehicle and the chaser attitude and gyros biases. This filter uses the range and angle measurements of the target relative to the chaser from a simulated Light Detection and Ranging (LIDAR) system, along with the star tracker and gyro measurements of the chaser. 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 navigations errors, trajectory dispersions, and attitude 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	Relative motion guidance, navigation and control for autonomous orbital rendezvous
title_short	Relative motion guidance, navigation and control for autonomous orbital rendezvous
title_full	Relative motion guidance, navigation and control for autonomous orbital rendezvous
title_fullStr	Relative motion guidance, navigation and control for autonomous orbital rendezvous
title_full_unstemmed	Relative motion guidance, navigation and control for autonomous orbital rendezvous
title_sort	relative motion guidance, navigation and control for autonomous orbital rendezvous
publisher	Instituto de Aeronautica e Espaco-IAE - Brazil
publishDate	2014
url	http://irep.iium.edu.my/38405/ http://irep.iium.edu.my/38405/ http://irep.iium.edu.my/38405/ http://irep.iium.edu.my/38405/1/38405_Relative%20motion%20guidance%2C%20navigation.pdf http://irep.iium.edu.my/38405/2/38405_Relative%20motion%20guidance%2C%20navigation_SCOPUS.pdf
first_indexed	2023-09-18T20:55:11Z
last_indexed	2023-09-18T20:55:11Z
_version_	1777410256287039488

Relative motion guidance, navigation and control for autonomous orbital rendezvous

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