Method for determining attitude of satellite based on visible light earth sensor and sun sensor

Abstract

A method for determining the attitude of a satellite based on a visible light earth sensor and a sun sensor uses combination of the visible light earth sensor and the sun sensor to determine the earth triaxial attitude of the satellite. The method comprises the following steps: processing an earth image formed by a CMOS imaging device, extracting the effective edge of the earth image, and fitting the center of the extracted effective edge by using a least square technology; approximately calculating the earth roll angle and the pitch angle under the assumption that the earth attitude angle of the satellite is a small angle; and calculating by using the sun sensor according to the earth roll angle and pitch angle attitude information obtained after approximate calculation to obtain the earth yaw angle of the satellite. Compared with traditional methods for determining the earth triaxial attitude angle of the satellite through using earth infrared sensor and sun sensor combination, the method provided by the invention has the advantages of improvement of the measurement precision of the attitude angle of the satellite, suitableness for attitude measurement of small satellites, and conformation to the current development trend of the small 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, infrared earth sensors have been widely used and become increasingly mature. Therefore, infrared earth sensors and sun sensors are used to jointly determine the three-axis attitude of the satellite to the ground. Become a common method. [0003] The existing method of using infrared earth sensor and sun sensor to jointly determine the satellite's three-axis attitude to the earth is: on the one hand, using the infrared earth sensor scanning mechanism to enter and exit the earth's carbon dioxide infrared radiation zone and the time when the infrared scanning mechanism reaches the reference point, Calculate the chord width of the infrared earth sensor scanning 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 satellite attitude determination method based on the visible light earth sensor and the sun sensor, and to solve the joint determination of the satellite attitude by the existing infrared earth sensor and the sun sensor Medium-time measurement accuracy, scanning mechanism angular velocity measurement accuracy, and satellite orbit parameter measurement accuracy lead to the problem that the satellite attitude angle measurement accuracy decreases, and this method is suitable for miniaturized small satellite attitude measurement, which conforms to the current development trend of small satellites

Images