A stellar gyro sensor

Abstract

A fixed star gyro sensor comprises a light shield, a first-stage optical system, a support structure, an image intensifier and the like, wherein the light shield is mounted at the front end of the support structure, the first-stage optical system is mounted inside the support structure, and the light shield is located at the first-stage optical system and used for elimination of stray light; the image intensifier is mounted at a focal plane of the rear end of the first-stage optical system, and a photocathode light-sensitive surface of the front end of the image intensifier is superposed with the focal plane of the first-stage optical system; a second-stage optical system is located at the back of the image intensifier, and an imaging fluorescent screen at the rear end of the image intensifier is located in an object plane of the second-stage optical system; an image panel of the second-stage optical system is superposed with a light-sensitive surface of a photodetector; and a detector circuit performs driving and imaging for the photodetector, and an information processing unit collects digital images acquired by the detector circuit and stores the digital images in the information processing unit.

Description

technical field [0001] The invention relates to a star sensor. Background technique [0002] At present, star sensors are often used for attitude measurement of spacecraft. The main principle of this sensor is: using the law that the position of stars is basically immobile relative to inertial space, the star map is obtained by photoelectric imaging of stars in a sky area, and then the star sensor The image is processed and identified to obtain the direction of the optical axis of the measurement sensor in the inertial space, and the three-axis attitude of the spacecraft can be obtained by converting the star sensor installation coordinate system on the spacecraft and the spacecraft attitude coordinate system. [0003] In the prior art, the star sensor hardware includes a light shield, an optical system (lens), an electronic system, electrical appliances, and a structural interface. The electronic system includes detector imaging components, information processing unit, pow...

AI Technical Summary

Problems solved by technology

[0006] The technical problem of the present invention is: to overcome the efficiency drop problem of the pixel point docking coupling of the stellar gyro imaging in the prior art and the problem of poor controllability of the coupling efficiency, the present invention proposes a stellar gyro sensor, through two The indirect coupling method of imaging makes the coupling efficiency between pixels controllable and adjustable, thereby improving the coupling efficiency between image intensifier pixels and detector pixels, and improving the detection sensitivity of stellar gyro

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