An attitude estimator that uses sun sensor outputs as the only attitude determination measurements to provide three-axis attitude information. This is accomplished by incorporating the Euler equation into the estimator. An unscented Kalman filter is employed to accommodate various nonlinear characteristics and uncertainties of the spacecraft dynamics and thus improve the robustness and accuracy of the attitude estimate.
Gyroless three-axis sun acquisition using sun sensor and unscented kalman filter
2017-05-09
Patent
Elektronische Ressource
Englisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
British Library Conference Proceedings | 2013
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