Method for configuration of star sensor head

Abstract

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.

Description

technical field [0001] The invention relates to the field of aerospace design, in particular to a method for head layout during star-sensitive periods. Background technique [0002] The head of the star sensor is a high-precision measurement device on the spacecraft, and its layout on the spacecraft has always been a key task in the design of the spacecraft configuration and layout. For an optical detector such as the head of the star sensor, there must not be any parts in the conical range with a half-cone angle of 30° around its detection axis, and there must be no strong light other than starlight through direct radiation or reflection. Enter the cone of view at the head of the star sensor. [0003] The layout of the star sensor head is quite difficult for a spacecraft with a single flight attitude, but for a spacecraft with multiple flight states, the conversion of different flight attitudes is achieved by rotating the spacecraft around its own reference axis at a certa...

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Problems solved by technology

[0007] For above-mentioned defect, the object of the present invention is to provide a kind of layout method of star sensor, to solve the technical problem that the layout method of star sensor head in the prior art can not rotate flexibly with spacecraft, therefore can not meet the requirement of multi-flying attitude

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