Method for configuration of star sensor head

A method for the configuration of a star sensor head comprises the following steps of: establishing a space digital ball by which a coordinate system is parallel to an orbital coordinate system; calculating the scope of an included angle between sunlight and the orbital coordinate system and the scope of an included angle between earthshine light and the orbital coordinate system; cutting the spaces of digital balls occupied by two partial areas in the space digital ball to form an effective space digital ball for the configuration of the star sensor head on a single flight attitude spacecraft; repeating the above steps; converting effective space digital balls obtained under a plurality of single flight attitudes into required rotating angles according to a spacecraft attitude, combining the digital balls rotated for corresponding angles; splicing the effective space digital balls together; taking a crossing part of the effective space digital balls; and determining the direction of the star sensor head on the spacecraft. With the adoption of the method, the requirements of a plurality of flight attitudes can be simultaneously satisfied, and the technical problem that the direction of the star sensor head cannot flexibly rotate along with the spacecraft can be solved.