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- W2387899319 abstract "The principle of attitude determination based on multi-vector sets is analyzed.With considering the errors from both inertial measurement units and the star sensor,the system model of SINS combined with star sensor is established.Based on the simulative real-time measurement information of the star sensor,both the attitude quaternion calculated by SINS,which is corresponding to the attitude rotation of the carrier frame and the inertial frame,and the high accuracy quaternion obtained by star sensor are fused,to achieve real-time estimation of gyroscope drift as well as the supervened online SINS correction of gyro drift errors and misalignment angles,to ensure the high precise of SINS consequently.Finally,the simulations indicate that the scheme of feedback alignment based on SINS/CNS integrated navigation system is feasible and effective." @default.
- W2387899319 created "2016-06-24" @default.
- W2387899319 creator A5026769100 @default.
- W2387899319 date "2010-01-01" @default.
- W2387899319 modified "2023-09-26" @default.
- W2387899319 title "A Method of SINS/Star Sensor Integrated Navigation Based on Attitude Quaternion" @default.
- W2387899319 hasPublicationYear "2010" @default.
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