The effects of instrumentation accuracy and configuration on estimation error are studied for the small expandable-tether deployment system (SEDS) using a continuous-discrete extended Kalman filter (CDEKF) state estimator. A twelfth order model that incorporates the rigid body modes of the tether as well as the satellite attitude dynamics is developed. Simulation results using the model and the estimator indicate that the originally planned instrumentation package could not estimate the state vector adequately. Recommendations are made and results presented that reduce the estimation error by adding instruments and increasing selected measurement accuracies.<>
On state estimation for an orbiting single tether system
IEEE Transactions on Aerospace and Electronic Systems ; 27 , 4 ; 689-695
01.07.1991
474163 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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