A Method of Avoiding the Interference of Earth's Atmospheric Light for Agile Small Satellite Sensors

Abstract

The invention discloses a method for avoiding the interference of an agile small satellite star sensor by the atmosphere and light, comprising: calculating the angle β between the optical axis vector of the star sensor and the star-ground vector, wherein the star-ground vector is The vector from the satellite to the center of the earth; obtain the stray light suppression angle α of the light shield, wherein the light shield is installed on the star sensor; calculate the star-ground vector and the direction from the satellite pointing to the earth and tangent to the earth's surface The included angle θ of the vector; judge the size relationship between β and α+θ, if β≤α+θ, then determine that this area is the area where the star sensor is affected by the earth, atmosphere and light; this program uses the agile small satellite star sensor to be affected by the earth The avoidance method of air-light interference is to isolate the measurement data of the star sensor affected by the earth-air-light interference from the system level, without changing the hardware matching and hardware configuration. The measurement accuracy of the satellite star sensor decreases, causing the problem of platform attitude fluctuations.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a method for avoiding the interference of an agile small satellite sensor from the earth, atmosphere and light. Background technique [0002] In the field of spaceflight, agile small satellites are being widely used due to their fast maneuverability in large angle attitudes, enabling satellites to obtain non-sub-satellite point data, and greatly increasing the amount of information that can be obtained by single orbit. The rapid maneuverability and multi-mode mission characteristics of agile small satellites make the satellite attitude reference no longer a single orbital coordinate system or inertial coordinate system, and will constantly switch between different reference coordinate systems. The star sensor is the most commonly used attitude measurement component on an agile small satellite. The star sensor obtains the attitude data of the spacecraft by imagi...

AI Technical Summary

Problems solved by technology

Due to the mission characteristics of the agile small satellite, there is no fixed position in the body, and it can avoid the influence of stray light from the earth in various modes at the same time. It is impossible to solve the problem that the optical system of the star sensor is susceptible to interference by optimizing the installation position of the star sensor on the satellite. At the same time, agile small satellites are constrained by cost and quality, the number of sensor configurations is limited, and the scheme of installing multiple products in multiple directions for data consistency comparison is not applicable

The measurement accuracy of the star sensor of the agile small satellite decreases when encountering the atmosphere and light, and the closed-loop control of the satellite control system will cause the attitude fluctuation of the platform

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