Method of correcting star sensor orbital period system error by means of gyro

Abstract

A method of correcting star sensor orbital period system error by means of gyro includes the steps of: 1) establishing a compensation difference value table, wherein the compensation difference value table is used for storing the relationship between star sensor three-axial attitude system error and the orbital phase of an aerocraft; 2) correcting the constant drift of the gyro by means of the attitude of the star sensor; 3) identifying the star sensor orbital period system error by means of integral value of the gyro, and updating the compensation difference value table; and 4) finding corresponding values in the updated compensation difference value table and directly deducting the corresponding values in the compensation difference value table from the star sensor three-axial attitude, thus obtaining the star sensor three-axial attitude excluding the system error. The method solves the technical problem that the star sensor system error cannot be identified and corrected in orbit in real time, and increases the real-time property and accuracy of correction on the star sensor system error, thus reducing work load of ground staffs.

Description

technical field [0001] The invention belongs to the field of spacecraft control, and relates to an on-orbit identification and real-time compensation method for the system error of a star sensor in a spacecraft attitude-orbit control system. Background technique [0002] The working principle of the star sensor is to obtain the high-precision attitude information of the star sensor in inertial space by taking pictures of the starry sky, extracting star points and comparing them with the built-in star library. The measurement accuracy of the star sensor itself is very high. As a key measurement component of the spacecraft attitude and orbit control system, its measurement accuracy directly determines the attitude determination accuracy of the spacecraft platform. [0003] However, the star sensor is a stand-alone unit outside the cabin, and its illumination and thermal control environment are relatively harsh. Due to the thermal deformation of the mounting surface of the star...

AI Technical Summary

Problems solved by technology

[0008] The technical problem solved by the present invention is to overcome the deficiencies of the prior art, provide a method for correcting the orbital period system error of the star sensor by using a gyroscope, and solve the technical problem that the system error of the star sensor cannot be identified and corrected in real time on orbit , improving the real-time and accuracy of star sensor system error correction, reducing the workload of ground personnel

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