Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements

Based on magnetometer measurements only, three-axis attitude, rate, and orbit estimation are successfully achieved. A single Augmented Dynamics Extended Kalman Filter (ADEKF) is configured by combining the spacecraft nonlinear attitude dynamics and quaternion kinematics with orbital mechanics. The...

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Main Authors:	Mohammad Abdelrahman, Mohammad Ibraheem, Park, Sang-Young
Format:	Article
Language:	English
Published:	Elsevier Masson SAS 2011
Subjects:	TL787 Astronautics
Online Access:	http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/1/b6111107506111847812c6c0b8b87987.pdf

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spelling	iium-85822011-12-08T09:03:17Z http://irep.iium.edu.my/8582/ Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements Mohammad Abdelrahman, Mohammad Ibraheem Park, Sang-Young TL787 Astronautics Based on magnetometer measurements only, three-axis attitude, rate, and orbit estimation are successfully achieved. A single Augmented Dynamics Extended Kalman Filter (ADEKF) is configured by combining the spacecraft nonlinear attitude dynamics and quaternion kinematics with orbital mechanics. The filter design is adopted for three-axis stabilized spacecraft in low Earth orbits where the aerodynamic drag is the dominant source of disturbances in addition to the spacecraft magnetic residuals. To reduce the computational burden, another Interlaced Extended Kalman Filter (IEKF) is developed to uncouple the attitude/rate from the orbit dynamics. Both filters are implemented using the magnetometer measurements and their corresponding time derivatives. As a part of EgyptSat-1 flight scenario, detumbling and standby modes are used for performance testing of the ADEKF. The concept of local observability is applied to the basic filter and the stability is investigated by incorporating extensive Monte Carlo simulations with uniformly distributed initial conditions. The filter shows the capability of estimating the attitude better than 5 deg and rate of order 0.03 deg/s in each axis. In orbit estimation, the filter is capable of estimating the position with accuracy less than 8 km and velocity upto 5 m/s in each axis. Elsevier Masson SAS 2011-01-31 Article PeerReviewed application/pdf en http://irep.iium.edu.my/8582/1/b6111107506111847812c6c0b8b87987.pdf Mohammad Abdelrahman, Mohammad Ibraheem and Park, Sang-Young (2011) Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements. Aerospace Science and Technology, 15 (8). pp. 653-669. ISSN 1270-9638 http://www.sciencedirect.com/science/article/pii/S1270963811000186 doi:10.1016/j.ast.2011.01.006
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL787 Astronautics
spellingShingle	TL787 Astronautics Mohammad Abdelrahman, Mohammad Ibraheem Park, Sang-Young Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
description	Based on magnetometer measurements only, three-axis attitude, rate, and orbit estimation are successfully achieved. A single Augmented Dynamics Extended Kalman Filter (ADEKF) is configured by combining the spacecraft nonlinear attitude dynamics and quaternion kinematics with orbital mechanics. The filter design is adopted for three-axis stabilized spacecraft in low Earth orbits where the aerodynamic drag is the dominant source of disturbances in addition to the spacecraft magnetic residuals. To reduce the computational burden, another Interlaced Extended Kalman Filter (IEKF) is developed to uncouple the attitude/rate from the orbit dynamics. Both filters are implemented using the magnetometer measurements and their corresponding time derivatives. As a part of EgyptSat-1 flight scenario, detumbling and standby modes are used for performance testing of the ADEKF. The concept of local observability is applied to the basic filter and the stability is investigated by incorporating extensive Monte Carlo simulations with uniformly distributed initial conditions. The filter shows the capability of estimating the attitude better than 5 deg and rate of order 0.03 deg/s in each axis. In orbit estimation, the filter is capable of estimating the position with accuracy less than 8 km and velocity upto 5 m/s in each axis.
format	Article
author	Mohammad Abdelrahman, Mohammad Ibraheem Park, Sang-Young
author_facet	Mohammad Abdelrahman, Mohammad Ibraheem Park, Sang-Young
author_sort	Mohammad Abdelrahman, Mohammad Ibraheem
title	Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
title_short	Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
title_full	Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
title_fullStr	Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
title_full_unstemmed	Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
title_sort	simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
publisher	Elsevier Masson SAS
publishDate	2011
url	http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/1/b6111107506111847812c6c0b8b87987.pdf
first_indexed	2023-09-18T20:18:19Z
last_indexed	2023-09-18T20:18:19Z
_version_	1777407937689419776

Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements

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