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Attitude estimation and control of a flexible spacecraft using inertial and optical measurements

It is envisaged that future earth resources satellites will be required to perform frequent attitude manoeuvres and also to maintain a given orientation to within a few seconds of arc. These requirements place a severe demand on the attitude measurement and control systems used, and this, demand is increased when the satellite needs to carry large flexible solar arrays. By combining inertial and optical measurements using an optimal filter, an attitude estimate can be obtained for which the error components are minimised over a wide frequency band. Jude, used intermittent star sensor readings to update the attitude and gyroscope drift estimates from an optimal filter and he noted that it would be useful to study the effect of mismatch between actual sensor models and those assumed in the computation of the optimal filter. Jude's recommendation is investigated in this paper.