Abstract
As part of the attitude determination system on board microsatellites, the kalman filter is implemented to generate an estimate attitude upon sensor observation. This paper presents an overview and analysis of the attitude estimator based on Kalman filtering for application on low Earth orbit microsatellites, specifically, Alsat-1 first Algerian microsatellite was used as an example. Various steps of the design and in orbit implementation of the estimator are described. This estimator is used during nominal attitude of the microsatellite.
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