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Attitude Determination using Kalman Filtering for Low Earth Orbit Microsatellites pp. 161-196 $100.00
Authors:  (Si Mohammed, Mohammed Arezki, Space Mechanic Division, Centre of Space Techniques, Arzew, Algeria)
Abstract:
As part of the attitude determination and control system on board microsatellites, the
kalman filter is implemented to generate an estimate attitude upon sensor observation.
This chapter presents an overview and analysis of some attitude estimators based on
Kalman filtering for application on low Earth orbit microsatellites. Various steps of the
design and in orbit implementation of the estimators are described. These estimators are
used during nominal attitude of the microsatellite. One type of attitude estimator is based
on small Euler angles. For this mode two estimator versions have been used, the full
estimator and its reduced version. This estimator is useful for on board computation
where energy resources are very limited. Another type of attitude estimator is based on
the quaternion parameter. The advantage of the quaternion parameter is the none
singularity. For this mode two estimator versions have been used, the six state and the
seven state estimators.
Numerical analysis and in orbit test results clearly indicate that the reduced version is
better than the full version for specifically attitude determination and control system
configuration of a microsatellite. Also, the results prove that the six state estimator is
better than the seven state estimator in terms of computational demand. 


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Attitude Determination using Kalman Filtering for Low Earth Orbit Microsatellites pp. 161-196