抄録
A real-time attitude estimation filter for the gyroless spacecrafts is proposed. In this method, outputs from a fly-wheel tachmeter is used. Attitude angular velocity is estimated from wheel angular velocity with use of algebraic relation between them based on angular momentum equation. Extended Kalman filter is used for compensation of sensor noises and drift of total angular momentum caused by external disturbances. The estimator's performance is demonstrated via numerical simulations.
