Fast Converging with High Accuracy Est imates of Satellite Attitude and Orbit Based on Magnetometer Augmented with Gyro, Star Sensor and GPS via Extended Kalman Filter
Habib, T. (2019). Fast Converging with High Accuracy Est imates of Satellite Attitude and Orbit Based on Magnetometer Augmented with Gyro, Star Sensor and GPS via Extended Kalman Filter. EKB Journal Management System, 14(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011), 1-9. doi: 10.21608/asat.2019.23240
T. Habib. "Fast Converging with High Accuracy Est imates of Satellite Attitude and Orbit Based on Magnetometer Augmented with Gyro, Star Sensor and GPS via Extended Kalman Filter". EKB Journal Management System, 14, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011, 2019, 1-9. doi: 10.21608/asat.2019.23240
Habib, T. (2019). 'Fast Converging with High Accuracy Est imates of Satellite Attitude and Orbit Based on Magnetometer Augmented with Gyro, Star Sensor and GPS via Extended Kalman Filter', EKB Journal Management System, 14(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011), pp. 1-9. doi: 10.21608/asat.2019.23240
Habib, T. Fast Converging with High Accuracy Est imates of Satellite Attitude and Orbit Based on Magnetometer Augmented with Gyro, Star Sensor and GPS via Extended Kalman Filter. EKB Journal Management System, 2019; 14(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011): 1-9. doi: 10.21608/asat.2019.23240

Fast Converging with High Accuracy Est imates of Satellite Attitude and Orbit Based on Magnetometer Augmented with Gyro, Star Sensor and GPS via Extended Kalman Filter

International Conference on Aerospace Sciences and Aviation Technology
Article 20, Volume 14, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011, May 2011, Page 1-9  XML PDF (222.85 K)
Document Type: Original Article
DOI: 10.21608/asat.2019.23240
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Author
T. Habib
Researcher, Dynamics and Control Department, National Authority for Remote Sensing and Space Sciences.
Abstract
The primary goal of this work is to extend the work done in, [1], to provide high accuracy satellite attitude and orbit estimates needed for imaging purposes and also before execution of spacecraft orbital maneuvers for the next Egyptian scientific satellite. The problem of coarse satellite attitude and orbit estimation based on magnetometer measurements has been treated in the literature. The current research expands the field of application from coarse and slow converging estimates to accurate and fast converging attitude and orbit estimates within 0.1o, and 10 m for attitude angles and spacecraft location respectively (1-σ). The magnetometer is used for both spacecraft attitude and orbit estimation, aided with gyro to provide angular velocity me a su r eme n t s , star sensor to provide attitude quaternion, and GPS receiver to provide spacecraft location. The spacecraft under consideration is subject to solar radiation pressure forces and moments, aerodynamic forces and moments, earth’s oblateness till the fourth order (i.e. 4 J ), gravity gradient moments, and residual magnetic dipole moments. The estimation algorithm developed is powerful enough to converge quickly (actually within 10 seconds) despite very large initial estimation errors with sufficiently high accuracy estimates.
Keywords
Fast Convergence; Attitude; Orbit; High Accuracy; Estimation; Magnetometer; Gyro; Star Sensor GPS; Earth Oblateness; Drag; Solar Radiation; Residual Dipole; Extended Kalman Filter
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