Abstract
In order to achieve the requirements of high precision and update rate satellite attitude determination, attitude determination solution based on star-sensor and gyro filtering algorithm is proposed. Quaternion model is established for satellite attitude determination, and Extended Kalman Filter is used to complete the fusion of sensor information as well as the correction of attitude error and gyro drift error. For the gyro's update rate is much higher than the star sensor’s, two multi-step-length attitude determination methods which are direct integration method and P-matrix (estimate error covariance matrix) one-step prediction method are designed, during the star-sensor’s output interval, the first method directly uses the gyro’s output to estimate the attitude quaternion, the second method predicts P-matrix (estimate error covariance matrix) additionally based on the first method. Combined with mathematical simulation and analysis, it is concluded that both multi-step-length satellite attitude determination methods can provide higher precision and update rate satellite attitude than fixed-step-length method. Considering the small difference between the estimation precisions of two multi-step-length methods, direct integration method is more applicable than P-matrix one-step prediction methods.
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