Method for determining satellite attitude based on visible light earth sensor

Abstract

The invention provides a method for determining satellite attitude based on a visible light earth sensor. The method employs the visible light earth sensor to determine the two-axis attitude of a satellite relative to the earth and comprises the following steps: processing an earth image produced by a CMOS imaging device so as to extract the effective boundary of the earth image; then extracting the center of the effective boundary by using least squares fitting; and on the hypothesis that the attitude angle of the satellite relative to the earth is a small angle, approximately calculating the roll angle and pitch angle of the satellite relative to the earth so as to eventually determine the two-axis attitude of the satellite relative to the earth. Compared with a traditional method using an infrared earth sensor for determination of the rolling and pitching two-axis attitude of satellites relative to the earth, the method provided by the invention has the advantages that the method improves the measurement precision of the two-axis attitude of the satellite relative to the earth, is applicable to measurement of the attitude miniature micro-satellites and conforms to the current development trend of micro-satellites.

Description

technical field [0001] The invention belongs to the field of satellite control and relates to a method for determining the attitude of a satellite. Background technique [0002] At present, among the sensors that use the earth as a reference vector to determine the satellite attitude angle, the infrared earth sensor has been widely used and is becoming more and more mature. Therefore, it has become a common method to use the infrared earth sensor to determine the two-axis attitude angle of the satellite to the ground. . [0003] The existing method of using the infrared earth sensor to determine the two-axis attitude angle of the satellite to the earth is: on the one hand, using the infrared earth sensor scanning mechanism to enter and exit the carbon dioxide infrared radiation belt of the earth and the time when the infrared scanning mechanism reaches the reference point, calculate the infrared earth The sensor scans the chord width of the earth and the geocentric vector E...

AI Technical Summary

Problems solved by technology

[0006] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a method for determining the satellite attitude based on the visible light earth sensor, and to solve the time measurement accuracy and the angular velocity measurement of the scanning mechanism in the determination of the satellite attitude by the existing infrared earth sensor Accuracy and satellite orbit parameter measurement accuracy lead to the problem that the accuracy of satellite attitude angle measurement decreases, and this method is suitable for miniaturized small satellite attitude measurement, which conforms to the current development trend of small satellites

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