Star sensor attitude determination method at self-determination retrieve rail controlling fault

Abstract

A star sensor attitude-determination method during the autonomous orbital control fault recovery includes: (1) predicting the satellite inertia attitude according to data measured by a gyro; (2) calculating the filtering modified innovation amount according to the inertia attitude of the satellite and the optical axis vector and the lateral axis vector under an inertial coordinate system which are measured and output by the star sensor, and calculating the error of the innovation amount between the front and the back periodicals, which is used for judging the consistency of star sensor data; (3) judging the consistency of the star sensor data; (4) fixing the attitude of the star sensor according to the two vectors; (5) introducing the star sensor which is combined with the gyro for the correction of the satellite attitude under the condition that the star sensor data arranges the initial value of the attitude estimation. The method can improves the reliability of the orbital control fault recovery, saves the time for the fault recovery and ensures that the orbital control is accurately recovered in time.

Description

technical field [0001] The invention relates to a method for re-determining the attitude of a satellite in the recovery process of a spacecraft orbit control failure. Especially after troubleshooting, when the orbit control is restored, the method of re-fixing the attitude of the star sensor information is introduced. Background technique [0002] At present, during satellite orbit change control, the attitude determination generally uses the measurement information of the gyroscope to estimate the attitude. If there is a fault in the orbit control process, stop this orbit control, and perform orbit control again after the fault is eliminated. The attitude estimation of the satellite has been corrected during the orbit control again, which is consistent with the actual attitude of the satellite. However, this method takes a long time to restore the orbit control of the satellite, which affects the time of fault recovery, and cannot meet the requirements of the uniqueness of...

AI Technical Summary

Problems solved by technology

In the fault recovery process, if the attitude estimation is performed only by gyro data, the satellite performs attitude estimation on the basis of an incorrect initial value, which will cause a large difference between the estimated attitude of the satellite and the actual attitude, thereby affecting the failure recovery and subsequent orbit control effects. , it is difficult to meet the requirement of uniqueness (accurate implementation of orbit control); if the attitude estimation is completed by the combination of gyro prediction and star sensor correction, compared with only gyro estimation attitude, the error between the estimated attitude and the actual attitude can be gradually reduced , but due to the limited amount of attitude correction, it takes a long time to eliminate the estimation error, and it takes a long time to recover from the fault, which will also affect the realization of the unique requirement of the orbit control window (timely orbit control)

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