Satellite attitude determination utilizing measurement sensor data and kalman filtering
In this paper we present a method for attitude determination using star tracker sensor measurements and Kalman filter. A contingency attitude determination mode is required in the event of a primary sensor failure. Presented here are the sensor modeling and Kalman filtering portions of the Atti...
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| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
2006
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/23318/1/Pages_from_Sp_Issue_%281%29.pdf http://irep.iium.edu.my/23318/ |
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| Summary: | In this paper we present a method for attitude
determination using star tracker sensor measurements and
Kalman filter. A contingency attitude determination mode
is required in the event of a primary sensor failure.
Presented here are the sensor modeling and Kalman
filtering portions of the Attitude Determination System
(ADS) study. The paper is conducted with the purpose of
evaluating the performance of a satellite ADS design.
The measurement sensors are central and primary to the
attitude pointing capability. We study in this paper a
satellite equipped with both star sensors and rate
measuring gyroscopes to perform the attitude
determination. This assessment was done by using Monte
Carlo methods to simulate these sensors. Using only star
measurements an optimal satellite orientation estimate is
found using the method of least squares, and the particular
algorithm invoked is referred to ESOQ2 method. A
successful Kalman filter algorithm for autonomous
attitude determination is developed herein. This algorithm
utilizes the three axis rate gyros for the satellite angular
rate data and star camera line-of-sight measurements.
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